X-Planes: Generation Orbit X-60
Filed under: aerospace, history, engineering
The register calls it an aircraft. The Air Force calls it a rocket twelve times.
The X-60A entry in the register of American military aerospace designations, which Andreas Parsch compiles from data the Department of Defense has released, opens with the words This aircraft is an autonomous hypersonic vehicle [Parsch, DOD 4120.15-L Addendum]. Twenty-seven days after that allocation the Air Force published the release announcing the designation, and its second sentence is this.
It is an air-dropped liquid rocket, specifically designed for hypersonic flight research to mature technologies including scramjet propulsion, high temperature materials and autonomous control.
That is from the announcement of 4 October 2018 [Air Force]. Across the 3 Air Force releases about this vehicle, totalling 1,032 words, the word rocket appears 12 times and the word aircraft appears 1 time [AFRL] [AFRL]. That single occurrence refers to the aeroplane the rocket hangs underneath.
This is the sixty-first article in the X-Planes series, following the X-1, the X-2, the X-3, the X-4, the X-5, the X-6, the X-7, the X-8, the X-9, the X-10, the X-11, the X-12, the X-13, the X-14, the X-15, the X-16, the X-17, the X-18, the X-19, the X-20, the X-21, the X-22, the X-23, the X-24, the X-25, the X-26, the X-27, the X-28, the X-29, the X-30, the X-31, the X-32, the X-33, the X-34, the X-35, the X-36, the X-37, the X-38, the X-39, the X-40, the X-41, the X-42, the X-43, the X-44, the X-45, the X-46, the X-47, the X-48, the X-49, the X-50, the X-51, the X-52, the X-53, the X-54, the X-55, the X-56, the X-57, the X-58, and the X-59.
This article is about a vehicle that never flew, and about why the paperwork could not say what it was. Both halves are measurable, and the second turns out to be a fact about the designation system rather than a mistake by whoever typed the row.
The Research Question
Most articles in this series have asked what binding unknown their aeroplane existed to resolve, and the exceptions are the designation anomalies, where there was no aeroplane to ask it of. The X-60A is neither. It was built, and it did not exist to resolve an unknown. It existed to sell access to one.
The condition it sold is a region of the Mach-altitude plane that hypersonic hardware has to survive and that no ground facility fully reproduces.
Air-breathing hypersonic propulsion runs at high dynamic pressure for a reason that can be written down. A scramjet’s thrust follows the mass of air it swallows, and the mass an inlet of a given capture area swallows is set by the density and the flight speed, which is twice the dynamic pressure divided by that speed.
\[\dot{m}_a \;=\; \rho V A_c \;=\; \frac{2 q}{V} \, A_c \tag{1}\]So the corridor is set by what the engine can breathe. At the middle of the band the flux is a usable number.
\[\frac{\dot{m}_a}{A_c} \bigg|_{M = 6} \;=\; \frac{2 \times 1500 \times 47.88\ \text{Pa}} {1,479.5\ \text{m/s} \times 6/5} \;=\; 80.9\ \text{kg}\,\text{m}^{-2}\text{s}^{-1} \tag{2}\]And the flux falls as the Mach number rises at fixed dynamic pressure, from 97 kilograms per square metre per second at Mach 5 to 60.7 at Mach 8, because the same $q$ is being delivered at a higher speed and therefore a lower density. An engine that wants more air as it goes faster has to be flown deeper into the atmosphere. The corridor exists to manage that tension.
Thermal protection has to be exposed to a real stagnation enthalpy for a real duration. Boundary-layer transition, which decides how much heating a vehicle sees, depends on a Reynolds number based on distance from the leading edge.
\[\mathit{Re}_x \;=\; \frac{\rho V x_t}{\mu} \tag{3}\]It also depends on the ratio of the wall temperature to the temperature the wall would reach if it were insulated.
\[\frac{T_w}{T_r} \tag{4}\]A ground tunnel does not get those two and the free-stream disturbance environment right at the same time, and the programme was built on that argument.
The Air Force Research Laboratory, which ran the programme and is abbreviated AFRL in its own releases, put the purpose unusually directly.
AFRL’s motivation for the X-60A program is to increase the frequency of flight testing while lowering the cost of maturing hypersonic technologies in relevant flight conditions. While hypersonic ground test facilities are vital in technology development, we must also test those technologies with actual hypersonic flight conditions.
The passage is from the critical design review release of 7 March 2019 [Hellman, AFRL]. The keystone is therefore not a speed and not an altitude. It is a rate and a price, and the physical quantity underneath both is seconds of usable test condition delivered per dollar.
The Air Force’s metaphor for the vehicle does more than decorate. It is exact.
The X-60A is like a flying wind tunnel to capture data that complements our current ground test capability.
That is Colonel Colin Tucker, then military deputy in the office of the deputy assistant secretary for science, technology and engineering, quoted in the designation announcement [Air Force, 4 October 2018]. A wind tunnel is a machine for producing a flow condition on demand, and its figure of merit is condition-seconds per run and dollars per run. The comparison commits the programme to being judged on those two numbers, and this article computes both.
Why the Corridor Is the Subject and the Vehicle Is Not
The contract that paid for the X-60A is titled Flight Testing of an Air Launch Testbed for Endoatmospheric Hypersonic Trajectories [USAspending, FA865017C2414]. The operative word is endoatmospheric. A sounding rocket that goes up and comes down passes through hypersonic Mach numbers on both legs and spends almost all of its flight where there is no air worth speaking of. This vehicle was built to stay in the air, at speed, on purpose.
The whole difficulty is staying in the air at speed, a condition on $q$ that the Mach number alone does not describe. The rest of this article treats the corridor as the subject and the airframe as a delivery mechanism for it. The X-54 and the X-59 required the same move when their subject turned out to be a pressure signature rather than an aeroplane.
Programme Origin
Generation Orbit Launch Services appears exactly once in the register’s 539 rows [Parsch, DOD 4120.15-L Addendum]. Every register count in this article is taken from every row of the copy the compiler last updated on 23 August 2026. That copy is later than this article’s date. The version current on that date, the compiler’s update of 11 August 2025 as the Internet Archive captured it on 25 November 2025, held 526 rows, twenty-nine of them X rows, and lacked fifteen later rows that include the X-68A and the X-76A [Parsch, DOD 4120.15-L Addendum, 11 August 2025]. Under that version 91 rows had an empty engines cell, 66 rows carried the Q symbol and 11 X rows described an uncrewed vehicle, the X-76A being absent. The company’s single row, the three X rows naming a rocket, the absence of the Q symbol from every X row and the 424 days from the XQ-58A are the same in both versions. The company was a subsidiary of SpaceWorks [Directory of U.S. Military Rockets and Missiles], and the federal small-business database gives it an Atlanta address and records it as having five employees [SBIR portfolio]. Against those five employees the same database records 38,353,364 dollars in total small-business awards across 3 Phase I and 2 Phase II instruments, of which 38,003,573 dollars is Phase II money.
The sequence is legible in the federal contract record [USAspending, FA865014M2503] [USAspending, FA865015C2542] [USAspending, FA865017C2414].
| Instrument | Signed | Obligated, dollars | Title |
|---|---|---|---|
| FA865014M2503 | 11 June 2014 | 149,984 | SBIR Phase I, Air Launch Testbed for Endoatmospheric Hypersonic Trajectories |
| FA865015C2542 | 23 July 2015 | 3,703,204 | Air Launch Testbed for Endoatmospheric Hypersonic Trajectories |
| FA865017C2414 | 27 March 2017 | 30,921,064.62 | Flight Testing of an Air Launch Testbed for Endoatmospheric Hypersonic Trajectories |
Those figures are total obligations rather than announced ceilings, and the two do not agree. The small-business database records the 2017 award as 34,530,060 dollars while the contract record shows 30,921,064.62 dollars actually obligated across 30 modifications [SBIR portfolio] [USAspending, FA865017C2414]. An announced value is a ceiling and an obligation is money, and this article uses the second wherever it can.
The First Small-Business Programme to Hold an X Number
The Air Force made a claim about the designation on the day it announced it.
This is the first Air Force Small Business Innovative Research program to receive an experimental “X” designation.
The designation release closes with that sentence [Air Force, 4 October 2018]. Its subject is the designation system. The vehicle does not enter into it. It deserves a pause, because the X series was created for the opposite kind of undertaking. The X-1 was a joint service and agency programme with a national research laboratory behind it [Bell X-1]. The X-15 flew for nine years on three airframes [North American X-15]. A Small Business Innovation Research contract is early-stage research funding for small firms [Small Business Innovation Research programme], and a firm may hold one only if it and its affiliates have no more than 500 employees [13 CFR 121.702].
Two things follow. The first is that the X series had become reachable by a route that did not exist when it was created. The second is that reaching it did not confer any of the things the earlier X programmes had, which were a flight test organisation, a range, a carrier fleet and an institutional appetite for failure. The X-60A had a number, a contract and five employees.
The Competition Was Two Bidders
The contract record shows the extent of competition on the 2017 award as a small-business set-aside with two offers received [USAspending, FA865017C2414]. That is not a criticism of the award. It is a measurement of how many organisations offered in 2017 to sell hypersonic flight condition by the second under this solicitation. Two did.
Sizing From First Principles
The public record gives two performance figures for the X-60A. The designation release says the vehicle provides access to high dynamic pressure conditions between Mach 5 and Mach 8 [Air Force, 4 October 2018]. The specification table of the specialist directory gives a ceiling of more than 21,300 metres, which is 69,882 feet and is quoted in the source as seventy thousand [Directory of U.S. Military Rockets and Missiles].
Those look like two independent specifications. They are not. Fixing a Mach number and an altitude fixes a dynamic pressure and leaves nothing free, and the relation that does the fixing is three lines long.
| Symbol | Meaning |
|---|---|
| $q$ | the free-stream dynamic pressure |
| $M$ | the flight Mach number |
| $V$ | the true airspeed |
| $V_0$ | the release velocity, the true airspeed at separation from the carrier |
| $a$ | the local speed of sound |
| $z$ | geometric altitude above mean sea level |
| $h$ | geopotential altitude |
| $h_b$ | the geopotential altitude of the base of an atmospheric layer |
| $\Delta z$ | the altitude gained between release and the corridor |
| $\Delta q$ | a change in dynamic pressure |
| $\gamma$ | the ratio of specific heats of air |
| $R$ | the specific gas constant of air |
| $R_e$ | the effective radius of the Earth used by the standard atmosphere |
| $T$ | the ambient absolute temperature |
| $T_b$ | the temperature at the base of an atmospheric layer |
| $p$ | the ambient static pressure |
| $p_b$ | the pressure at the base of an atmospheric layer |
| $p_a$ | the ambient pressure at the nozzle exit plane |
| $\rho$ | the ambient air density |
| $\lambda$ | the temperature lapse rate of an atmospheric layer |
| $g$ | the acceleration due to gravity |
| $g_0$ | standard gravity, the constant that defines specific impulse |
| $H$ | the pressure scale height of the atmosphere |
| $\mu$ | the dynamic viscosity of air |
| $S_u$ | the Sutherland constant for air |
| $C_1$ | the Sutherland coefficient for air |
| $T_0$ | the stagnation temperature |
| $p_0$ | the stagnation pressure |
| $h_0$ | the stagnation enthalpy per unit mass |
| $c_p$ | the specific heat of air at constant pressure |
| $\dot{Q}$ | the stagnation-point convective heat flux |
| $R_n$ | the nose radius of the test article |
| $k_s$ | the Sutton-Graves constant for air |
| $\mathit{Re}$ | the Reynolds number |
| $L_r$ | a reference length |
| $\mathit{Pr}$ | the Prandtl number of air |
| $r_f$ | the recovery factor, which is the fraction of the stagnation temperature rise a wall actually sees |
| $T_r$ | the adiabatic wall recovery temperature |
| $T_w$ | the wall temperature of the test article |
| $\mathit{Re}_x$ | the Reynolds number based on distance from the leading edge |
| $x_t$ | the distance from the leading edge at which the boundary layer goes turbulent |
| $A_c$ | the inlet capture area of an air-breathing test article |
| $\dot{m}_a$ | the mass flow of air an inlet captures |
| $F$ | the engine thrust |
| $F_v$ | the vacuum thrust of the engine |
| $\dot{m}$ | the propellant mass flow rate |
| $v_e$ | the effective exhaust velocity |
| $v_j$ | the nozzle exit velocity of the jet |
| $A_e$ | the nozzle exit area |
| $A_t$ | the nozzle throat area |
| $\epsilon$ | the nozzle area ratio |
| $p_c$ | the chamber pressure |
| $p_e$ | the nozzle exit pressure |
| $I_s$ | the specific impulse |
| $C_F$ | the nozzle thrust coefficient |
| $c_*$ | the characteristic velocity of the propellant combination |
| $m$ | the instantaneous vehicle mass |
| $m_0$ | the vehicle mass at engine ignition |
| $m_f$ | the vehicle mass at burnout |
| $m_p$ | the usable propellant mass |
| $m_s$ | the structural and inert mass of the vehicle |
| $m_l$ | the payload mass |
| $\zeta$ | the propellant mass fraction |
| $\sigma_s$ | the structural coefficient, the inert mass as a share of inert plus propellant |
| $f_l$ | the payload mass fraction |
| $\rho_b$ | the bulk density of the loaded propellant |
| $\Gamma$ | the Vandenkerckhove function of the ratio of specific heats |
| $T_c$ | the combustion chamber temperature |
| $M_x$ | the Mach number at the nozzle exit plane |
| $\phi$ | the throttle setting, as a fraction of rated thrust |
| $\Delta p_j$ | the pressure drop across the injector |
| $C_j$ | the discharge coefficient of an injector orifice |
| $A_j$ | the total injector orifice area |
| $t_b$ | the powered burn duration |
| $\Delta V$ | the velocity increment the rocket must supply |
| $\Delta V_g$ | the velocity lost to gravity during powered ascent |
| $\Delta V_d$ | the velocity lost to drag during powered ascent |
| $\Delta V_k$ | the kinematic velocity increment, including the climb |
| $D$ | the aerodynamic drag |
| $L$ | the aerodynamic lift |
| $W$ | the vehicle weight |
| $C_d$ | the drag coefficient |
| $C_l$ | the lift coefficient |
| $S$ | the aerodynamic reference area |
| $A_f$ | the frontal area of the booster |
| $d$ | the booster diameter |
| $l_b$ | the booster length |
| $l_t$ | the length of the propellant tankage |
| $f_r$ | the fineness ratio of the booster |
| $b$ | the fin span |
| $\theta$ | the flight path angle above the horizontal |
| $\theta_0$ | the flight path angle at release from the carrier |
| $\theta_b$ | the commanded flight path angle at burnout |
| $\theta_c$ | the flight path angle the pitch programme commands |
| $n$ | the aerodynamic load factor |
| $\beta_b$ | the ballistic coefficient |
| $t$ | time from engine ignition |
| $r_m$ | the oxidiser to fuel mixture ratio by mass |
| $m_o$ | the oxidiser mass |
| $m_u$ | the fuel mass |
| $\rho_o$ | the density of liquid oxygen at its normal boiling point |
| $\rho_u$ | the density of the kerosene fuel |
| $V_p$ | the total propellant volume |
| $C_t$ | the total cost obligated against the programme |
| $N_f$ | the number of flights flown |
| $\tau$ | the time a payload spends inside the test corridor on one flight |
| $c_s$ | the cost per second of test condition delivered |
| $c_m$ | the marginal cost of one further flight |
| $M_d$ | the Mach number above which a flight counts as being at condition |
| $M_i$ | the Mach number at an anchor point of the drag model, the next anchor being $M_i’$ |
| $\mu_E$ | the gravitational parameter of the Earth |
| $R_m$ | the volumetric mean radius of the Earth |
| $r_b$ | the geocentric radius at burnout |
| $r_p$ | the perigee radius of the coasting ellipse |
| $\varepsilon$ | the specific orbital energy of the burnout state |
| $\ell$ | the specific angular momentum of the burnout state |
| $a_s$ | the semi-major axis of the coasting ellipse |
| $e_c$ | the eccentricity of the coasting ellipse |
| $V_c$ | the circular orbital speed at the burnout radius |
Dynamic Pressure Does Not Depend on Temperature
Dynamic pressure is defined from the density and the true airspeed.
\[q = \tfrac{1}{2} \rho V^2 \tag{5}\]For a perfect gas the density is set by the pressure and the temperature.
\[\rho = \frac{p}{R T} \tag{6}\]And the speed of sound is set by the temperature alone, so the true airspeed is the Mach number times a function of temperature.
\[a = \sqrt{\gamma R T}, \qquad V = M a \tag{7}\]Substituting both into the definition, the temperature cancels exactly.
\[q \;=\; \tfrac{1}{2} \rho V^2 \;=\; \tfrac{1}{2} \left( \frac{p}{R T} \right) \left( \gamma R T \right) M^2 \;=\; \tfrac{1}{2} \gamma p M^2 \tag{8}\]With $\gamma = 1.4$ for air, the working form is one multiplication.
\[q \;=\; 0.7 \, p \, M^2 \tag{9}\]The result is counter-intuitive in a useful direction. A hypersonic vehicle’s aerothermal environment is dominated by temperature, and its structural loading is dominated by dynamic pressure, and the two are decoupled in the sense that the second does not know about the first. Whether the air at 25 kilometres is at 220 kelvin or 240 kelvin changes the speed of sound, the true airspeed at a given Mach number and the density, and it changes all three in a way that leaves $q$ untouched. A dynamic pressure specification fixes ambient static pressure and Mach number, and therefore altitude and Mach number.
The check is arithmetic, and it is performed here. At 21,300 metres the standard atmosphere gives a density of 0.07216 kilograms per cubic metre and a speed of sound of 295.9 metres per second, so Mach 5 is 1,479.5 metres per second and $\tfrac{1}{2}\rho V^2$ is 78,975.6 pascals. The static pressure at the same altitude is 4,512.9 pascals, so $\tfrac{1}{2}\gamma p M^2$ is 78,975.6 pascals. The two differ by 0 pascals.
What the Two Published Numbers Multiply Out To
\[p \;=\; \frac{2 q}{\gamma M^2} \tag{10}\]Read the other way, the published pair is a dynamic pressure.
\[q \;=\; \tfrac{1}{2} \times 1.4 \times 4,512.9\ \text{Pa} \times 5^2 \;=\; 78,976\ \text{Pa} \;=\; 1,649\ \text{lbf/ft}^2 \tag{11}\]1,649 pounds per square foot is squarely inside the band that air-breathing hypersonic propulsion is tested in, which the textbook literature places at roughly one to two thousand [Heiser and Pratt] [Anderson]. The two numbers the Air Force published are not a speed and a ceiling. They are a scramjet test condition, written in the only units a press release can use.
The Atmosphere the Corridor Is Drawn In
Everything above needs a pressure as a function of altitude, and this article uses the 1976 standard atmosphere throughout [U.S. Standard Atmosphere 1976 1976]. The model is hydrostatic.
\[\frac{dp}{dh} = -\, g \rho = -\, \frac{g p}{R T} \tag{12}\]Geopotential altitude exists to fold gravity into the altitude coordinate, so that gravity need not be carried as a variable.
\[h = \frac{R_e \, z}{R_e + z} \tag{13}\]Temperature is piecewise linear in geopotential altitude.
\[T(h) = T_b + \lambda \, (h - h_b) \tag{14}\]Integrating the hydrostatic equation through a layer with a nonzero lapse rate gives a power law.
\[p(h) \;=\; p_b \left[ 1 + \frac{\lambda \, (h - h_b)}{T_b} \right]^{-g_0 / (R \lambda)} \qquad (\lambda \neq 0) \tag{15}\]And through an isothermal layer, such as the one between 11 and 20 geopotential kilometres in which the X-60A is released, an exponential [International Standard Atmosphere].
\[p(h) \;=\; p_b \, \exp\!\left[ -\, \frac{g_0 \, (h - h_b)}{R \, T_b} \right] \qquad (\lambda = 0) \tag{16}\]The exponential decay constant is the scale height.
\[H = \frac{R T}{g_0} \tag{17}\]At the corridor altitude the scale height is 6,378 metres. That single number governs how hard the corridor is to hold, because at fixed Mach the dynamic pressure inherits the pressure’s altitude dependence exactly.
\[\frac{1}{q} \frac{\partial q}{\partial z} \bigg|_{M} \;=\; \frac{1}{p} \frac{dp}{dz} \;=\; -\, \frac{1}{H} \tag{18}\]That is the differential form. The finite-difference form is what a guidance law has to work with.
\[\frac{\Delta q}{q} \;=\; 1 - \exp\!\left( -\, \frac{\Delta z}{H} \right) \;=\; 14.51\ \text{percent per kilometre} \tag{19}\]A kilometre of altitude is 14.51 percent of dynamic pressure. Holding $q$ to within ten percent at fixed Mach therefore means holding altitude to within about seven hundred metres, on a vehicle climbing at several hundred metres per second. That is the control problem stated as a number. It is why a corridor is not merely narrow but difficult.
The same relation read along the corridor rather than across it gives the slope of a constant-$q$ line in the Mach-altitude plane.
\[\frac{d(\ln M)}{dz} \bigg|_{q} \;=\; \frac{1}{2H} \tag{20}\]Where the Corridor Sits
Inverting the pressure profile for a chosen dynamic pressure and Mach number gives the altitude at which that pair occurs. The table is the corridor.
| Dynamic pressure | Mach 5 | Mach 6 | Mach 8 |
|---|---|---|---|
| 500 lbf/ft² | 95.5 kft | 103.5 kft | 116.5 kft |
| 1,000 lbf/ft² | 80.5 kft | 88.4 kft | 100.9 kft |
| 1,500 lbf/ft² | 71.9 kft | 79.6 kft | 92 kft |
| 2,000 lbf/ft² | 65.8 kft | 73.5 kft | 85.8 kft |
Every altitude in that table is between about twenty and thirty-six kilometres. The bottom of that range is not out of reach of an air-breathing aeroplane, since the absolute altitude record in horizontal flight, set by an SR-71 on 28 July 1976, is 85,069 feet [List of flight altitude records], which is above five of the twelve cells in the table. The top of it is. And the whole of it is below any satellite. A sounding rocket passes through that band in seconds on its way somewhere else.
What the Corridor Does to Whatever Is In It
The point of reaching the corridor is to put hardware in it, so the environment the hardware sees is the product being sold.
Stagnation temperature follows from the energy equation for a perfect gas.
\[\frac{T_0}{T} \;=\; 1 + \frac{\gamma - 1}{2} M^2 \tag{21}\] \[h_0 = c_p T_0 \tag{22}\]At the middle of the band, on a 1,500 pound per square foot line, the numbers are the argument for the whole programme.
| Mach | Stagnation temperature | Stagnation enthalpy | Stagnation pressure ratio | Unit Reynolds number |
|---|---|---|---|---|
| 5 | 1,311 K, 1,038 °C | 1.317 MJ/kg | 529.1 | 6.77 × 10⁶ /m |
| 6 | 1,811 K, 1,538 °C | 1.819 MJ/kg | 1,578.9 | 5.56 × 10⁶ /m |
| 8 | 3,099 K, 2,826 °C | 3.114 MJ/kg | 9,762.9 | 4.08 × 10⁶ /m |
The stagnation pressure ratio comes from the isentropic relation.
\[\frac{p_0}{p} \;=\; \left( 1 + \frac{\gamma - 1}{2} M^2 \right)^{\gamma / (\gamma - 1)} \tag{23}\]The first column overstates what a wall actually reaches, and by a knowable amount. A surface in a moving boundary layer recovers only part of the stagnation temperature rise, and the fraction is set by the Prandtl number.
\[r_f \;=\; \mathit{Pr}^{1/2} \;\; \text{(laminar)}, \qquad r_f \;=\; \mathit{Pr}^{1/3} \;\; \text{(turbulent)} \tag{24}\] \[T_r \;=\; T \left( 1 + r_f \, \frac{\gamma - 1}{2} M^2 \right) \tag{25}\]With a Prandtl number of 0.71 the recovery factor is 0.843 laminar and 0.892 turbulent, so the turbulent recovery temperature at Mach 6 is 1,639 kelvin against a stagnation value of 1,811. The correction is 9.5 percent and it runs the safe way, so stagnation temperature is the figure a specification quotes and recovery temperature is the figure a designer sizes to.
The third column is why ground facilities are hard. To reproduce Mach 8 at 1,500 pounds per square foot a blowdown tunnel needs a reservoir at 9,762.9 times the test-section static pressure and at 3,099 kelvin, and it needs to hold both for long enough to take data. Facilities that reach the enthalpy do so for milliseconds, and facilities that run for minutes do not reach the enthalpy [Bertin] [Anderson].
The Reynolds number in the fourth column uses Sutherland’s law for viscosity.
\[\mu = \frac{C_1 \, T^{3/2}}{T + S_u} \tag{26}\] \[\mathit{Re} = \frac{\rho V L_r}{\mu} \tag{27}\]The fourth column of the table above is that quantity per metre of length, which is how a flight condition is reported when the test article’s length is not yet decided.
\[\frac{\mathit{Re}}{L_r} \;=\; \frac{\rho V}{\mu} \tag{28}\]Unit Reynolds number is a quantity ground facilities are known to have difficulty matching alongside the others, and it decides where the boundary layer goes turbulent, which decides the heating, which decides the thermal protection mass. A tunnel matching Mach number and stagnation enthalpy at the wrong Reynolds number produces a laminar answer to a turbulent question.
The heating a test article receives at a stagnation point scales with the square root of density and the cube of velocity, in the Sutton-Graves form used throughout entry work [Atmospheric entry] [Vinh, Busemann and Culp].
\[\dot{Q} \;=\; k_s \sqrt{\frac{\rho}{R_n}} \; V^3 \tag{29}\]The cube on velocity is the reason the corridor is expensive and the square root on density is the reason it is a corridor at all. Doubling the Mach number multiplies the heat flux eightfold at fixed density, and the only way to buy that back is to climb, which costs the dynamic pressure the air-breathing payload came for.
Dependent Systems
The Engine Is the Only Part That Is Not a Structure
The X-60A’s propulsion is the Hadley, a liquid oxygen and kerosene engine from Ursa Major Technologies, and the Air Force named it in all three of its releases [Air Force] [AFRL] [AFRL]. Its maker describes it as an oxygen-rich staged combustion cycle engine of 5,000 pounds of thrust, first qualified in 2021 [Ursa Major] [Staged combustion cycle]. That cycle is unusual in an American engine of any size, and the article says no more than that, because the stronger claim available in secondary reporting is not in any document read for this article.
Thrust for any rocket engine is momentum flux plus a pressure term at the exit plane.
\[F = \dot{m} \, v_j + \left( p_e - p_a \right) A_e \tag{30}\] \[v_e = \frac{F}{\dot{m}}, \qquad I_s = \frac{F}{\dot{m} \, g_0} \tag{31}\]The chamber and nozzle contributions separate cleanly, and engine test data are reported in that form.
\[c_* = \frac{p_c A_t}{\dot{m}}, \qquad C_F = \frac{F}{p_c A_t}, \qquad F = \dot{m} \, c_* \, C_F \tag{32}\] \[\epsilon = \frac{A_e}{A_t} \tag{33}\]The area ratio and the exit Mach number are the same fact written two ways, through the relation every convergent-divergent nozzle obeys.
\[\epsilon \;=\; \frac{A_e}{A_t} \;=\; \frac{1}{M_x} \left[ \frac{2}{\gamma + 1} \left( 1 + \frac{\gamma - 1}{2} M_x^2 \right) \right]^{(\gamma + 1) / (2(\gamma - 1))} \tag{34}\]Neither the chamber pressure nor the throat area is published, and one can be traded for the other rather than invented. The mass flow through a choked throat is fixed by the chamber conditions and the throat area.
\[\dot{m} \;=\; \frac{\Gamma \, p_c A_t}{\sqrt{R \, T_c}}, \qquad \Gamma \;=\; \sqrt{\gamma} \left( \frac{2}{\gamma + 1} \right)^{(\gamma + 1) / (2(\gamma - 1))} \tag{35}\]With $\Gamma$ equal to 0.6847 for air, and taking a characteristic velocity of 1,800 metres per second, which is typical for liquid oxygen and kerosene and is not published for this engine, the product of chamber pressure and throat area follows from the mass flow alone.
\[p_c A_t \;=\; \dot{m} \, c_* \;=\; 14,078\ \text{N} \tag{36}\]That is one number standing in for two. At a chamber pressure of four megapascals the throat is 66.9 millimetres across, at seven it is 50.6, and at ten it is 42.3. A staged combustion cycle is chosen when high chamber pressure is wanted, so the throat is more likely nearer the last figure than the first, and the article does not pretend to know which.
The quoted 5,000 pounds is a sea-level rating and this vehicle never sees sea level. The pressure term is negative at sea level and vanishes in vacuum, so the same engine produces more thrust the higher it goes.
\[F(z) \;=\; F_v - p(z) \, A_e, \qquad F_v = F(0) + p_b(0) \, A_e \tag{37}\]The correction cannot be computed, and why it cannot is stated here in place of a guess. Ursa Major lists three qualified Hadley variants, being a 5,000 pound sea-level engine, a 6,500 pound vacuum engine and a hypersonic version developed with Stratolaunch [Ursa Major]. Those are three different nozzles and not one engine at three altitudes, so the 1,500 pound difference between the first two does not give $A_e$ for the first. It follows only that the X-60A’s thrust above twelve kilometres exceeds 5,000 pounds by an unpublished margin, and therefore that every performance figure in this article computed from 5,000 pounds is a floor rather than an estimate.
The thrust-to-weight ratio at release follows from the published gross mass of 1,360 kilograms [Directory of U.S. Military Rockets and Missiles].
\[\frac{F}{W} \;=\; \frac{22,241\ \text{N}}{13,337\ \text{N}} \;=\; 1.668 \tag{38}\]1.668 is a low number for a rocket and a very high one for an aeroplane, and the X-60A is the second of those in the register and the first of those in the physics. A launch vehicle lifting from a pad needs a ratio above one to leave the pad at all. This vehicle is released in flight already moving, so it needs only enough to overcome drag and the component of weight along its path, and 1.668 is generous for that.
How Much Propellant the Corridor Costs
The classical estimate comes first, because it is checkable by hand and because the integration that replaces it should be seen to agree with it in order of magnitude.
Release is at high subsonic speed in a climb [Directory of U.S. Military Rockets and Missiles]. Taking twelve kilometres and Mach 0.8, the release speed is 236.1 metres per second against a corridor speed of 1,479.5 metres per second, a kinematic difference of 1,243.5 metres per second. Potential energy is velocity too, and the climb of 9,300 metres is worth 427.1 metres per second on its own, so the two are added through the energy rather than side by side.
\[\Delta V_k \;=\; \sqrt{ V^2 + 2 g_0 \, \Delta z } \; - \; V_0 \tag{39}\] \[\Delta V_k \;=\; \sqrt{ (1,479.5)^2 + 2 \times 9.80665 \times 9,300 } \; - \; 236.1 \;=\; 1,303.9\ \text{m/s} \tag{40}\]Losses to gravity and drag are not part of that number and have to be carried explicitly.
\[\Delta V \;=\; \Delta V_k + \Delta V_g + \Delta V_d, \qquad \Delta V_g = \int_0^{t_b} g \sin\theta \; dt, \qquad \Delta V_d = \int_0^{t_b} \frac{D}{m} \; dt \tag{41}\]The rocket equation then converts a velocity increment into a mass ratio.
\[\Delta V \;=\; I_s \, g_0 \, \ln\!\left( \frac{m_0}{m_f} \right) \tag{42}\] \[\frac{m_0}{m_f} \;=\; \exp\!\left( \frac{\Delta V}{I_s g_0} \right), \qquad \zeta \;=\; \frac{m_p}{m_0} \;=\; 1 - \exp\!\left( -\, \frac{\Delta V}{I_s g_0} \right) \tag{43}\] \[m_0 = m_p + m_s + m_l \tag{44}\]At an assumed specific impulse of 290 seconds, which is typical for liquid oxygen and kerosene and is not published for this engine, the effective exhaust velocity is 2,843.9 metres per second and the mass ratio for a 300 metre per second loss allowance is 1.7576. That is a propellant fraction of 0.4311 and a propellant load of 586.2 kilograms out of 1,360.
\[\dot{m} = \frac{F}{I_s \, g_0}, \qquad t_b = \frac{m_p}{\dot{m}} \tag{45}\] \[t_b \;=\; \frac{586.2\ \text{kg}}{7.821\ \text{kg/s}} \;=\; 75\ \text{s} \tag{46}\]A burn of 75 seconds is long for a vehicle this size and that is the design. The Black Brant sounding rocket motor, whose loaded weight of 2,827 pounds is 1,282 kilograms and close to this vehicle’s gross mass, has an action time of 27.5 seconds [NASA Sounding Rockets User Handbook]. This one burns for over a minute, because the product is time at condition and a coast is time spent decelerating.
The comparison is with a real instrument and not a figure of speech. The agency that flies sounding rockets publishes a handbook for the people who put payloads on them, and the vehicles in it are solid motors that burn briefly and hard and then leave the payload on a ballistic arc [NASA Sounding Rockets User Handbook]. The X-60A inverts that. It is the same size of vehicle, launched into the same band of altitudes, built to do the opposite thing with the time.
The Diameter the Record Does Not Publish
The specialist directory’s specification table gives length, span, mass and speed and leaves the diameter as a question mark [Directory of U.S. Military Rockets and Missiles]. It can be recovered, because the propellant has to fit.
Liquid oxygen and kerosene burn near a mixture ratio of 2.3 to 1, which splits the propellant mass.
\[m_o \;=\; m_p \, \frac{r_m}{1 + r_m}, \qquad m_u \;=\; \frac{m_p}{1 + r_m} \tag{47}\] \[V_p \;=\; \frac{m_o}{\rho_o} + \frac{m_u}{\rho_u} \tag{48}\] \[d \;=\; 2 \sqrt{ \frac{V_p}{\pi \, l_t} } \tag{49}\] \[f_r = \frac{l_b}{d}, \qquad A_f = \frac{\pi d^2}{4} \tag{50}\]The recovery is an estimate with three assumptions in it, and all three are stated. The mixture ratio is assumed, the tankage is assumed to occupy seventy percent of the 4.9 metre booster [Directory of U.S. Military Rockets and Missiles], and the tanks are assumed cylindrical at the full body diameter. Under those assumptions the propellant volume is 0.6763 cubic metres and the diameter is 0.501 metres, giving a fineness ratio of 9.8 and a span of 3.39 diameters.
The same two numbers give the density the tankage has to carry.
\[\rho_b \;=\; \frac{m_p}{V_p} \;=\; 1,015.3\ \text{kg}\,\text{m}^{-3} \tag{51}\]A loaded liquid oxygen and kerosene stage is very nearly the density of water, at 1.015 times it. That ratio is a useful sanity check on any propellant volume, and it explains why launch vehicles are mostly empty space by mass and mostly full by volume.
The span follows the same way.
\[\frac{b}{d} \tag{52}\]Those three numbers are mutually consistent with a vehicle that exists in photographs. No other check is available. A body of nine to ten calibres with a small cruciform or planar fin set at three and a half diameters of span is an ordinary slender supersonic configuration, and a wildly wrong diameter would have produced a body of four calibres or of twenty.
The diameter and the propellant load are not independent. The propellant volume sets the diameter, the diameter sets the frontal area, the frontal area sets the drag, and the drag sets how much propellant the corridor costs. It is a fixed point, and solving it as one takes 13 iterations and moves the diameter 8.2 percent from the single-pass value of 0.463 metres.
Flying It
The ascent is two ordinary equations, one along the flight path and one across it.
\[m \frac{dV}{dt} \;=\; F - D - m g \sin\theta \tag{53}\] \[m V \frac{d\theta}{dt} \;=\; L - m g \cos\theta \tag{54}\] \[L = \tfrac{1}{2} \rho V^2 S C_l, \qquad D = \tfrac{1}{2} \rho V^2 S C_d \tag{55}\] \[\beta_b = \frac{m}{C_d S} \tag{56}\]Two kinematic relations close the set, one for altitude and one for the mass the engine is consuming.
\[\frac{dz}{dt} \;=\; V \sin\theta, \qquad \frac{dm}{dt} \;=\; -\, \dot{m} \tag{57}\]The pitch programme is the only thing left free. It is commanded rather than solved, running linearly from the release angle to the burnout angle over the burn.
\[\theta_c(t) \;=\; \theta_0 + \left( \theta_b - \theta_0 \right) \min\!\left( 1, \; \frac{t}{t_b} \right) \tag{58}\]The drag coefficient is interpolated between anchor points that reproduce the shape every slender supersonic body shares, being a low subsonic value, a transonic peak near Mach 1.2 and a slow supersonic decline.
\[C_d(M) \;=\; C_d(M_i) + \left[ C_d(M_i') - C_d(M_i) \right] \frac{M - M_i}{M_i' - M_i}, \qquad M_i \le M \le M_i' \tag{59}\]This article integrates those equations, and what that integration is and is not needs to be clear. No trajectory for the X-60A appears in the programme’s releases. What follows is a two-degree-of-freedom point-mass ascent on a commanded pitch programme, using the published mass, the published sea-level thrust and the fixed-point geometry above, with a drag coefficient taken from the shape every slender supersonic body shares rather than from this vehicle. It shows what the published corridor costs. It does not show what the programme intended to fly.
The lift is not modelled. It is solved for by rearranging the flight-path equation to give the lift the commanded pitch programme requires at each instant.
\[L \;=\; m V \frac{d\theta}{dt} + m g \cos\theta \tag{60}\]A lift coefficient guessed from an artist’s impression would put a fabricated number on both sides of the statutory comparison of thrust with lift made below.
Integrating to the Mach numbers the Air Force published gives the propellant each one costs.
| Target | Specific impulse 270 s | 290 s | 310 s |
|---|---|---|---|
| Mach 5 | 46.1 % | 43.8 % | 41.7 % |
| Mach 6 | 52.9 % | 50.5 % | 48.2 % |
| Mach 8 | 65 % | 62.7 % | 60.6 % |
The mass budget closes, and it might not have. At the nominal specific impulse, reaching Mach 8 costs 852.9 kilograms of propellant and leaves 507.1 kilograms for everything else. Subtracting the published 320 kilogram payload [Directory of U.S. Military Rockets and Missiles] leaves 187.1 kilograms for the tank, the engine, the thrust vector actuators, the avionics, the fins and the flight termination system, which is 13.8 percent of gross.
A stage is judged on two ratios rather than on either mass alone.
\[\sigma_s \;=\; \frac{m_s}{m_s + m_p}, \qquad f_l \;=\; \frac{m_l}{m_0} \tag{61}\]The payload fraction is 23.5 percent and the structural coefficient at Mach 8 is 18 percent, against 34 at Mach 6 and 42.7 at Mach 5. The first two stages of the air-launched Pegasus XL, whose published empty, propellant and gross masses agree, come to 0.084 and 0.096 [Pegasus rocket], so the hardest case here is more generous than a launcher stage has to be, and the published payload and the top of the published speed range are compatible. The budget closes with room.
The computed losses are modest, which the geometry explains. Drag costs 243.6 metres per second and gravity 185, for 428.6 in total, against the 1,603.9 metre per second allowance the hand calculation assumed. The reason is that a carrier aircraft removes most of the atmosphere before the rocket lights. The mass of the air column above an altitude is its pressure divided by gravity, so the share left below the release point is one minus a pressure ratio.
\[\frac{m}{S} \bigg|_{\text{above } z} \;=\; \frac{p(z)}{g_0}, \qquad 1 - \frac{p(z)}{p_b(0)} \;=\; 80.9\ \text{percent} \tag{62}\]A vehicle released at twelve kilometres has already been carried above 80.9 percent of the atmosphere’s mass, leaving 1,978 kilograms per square metre overhead against 10,332 at sea level. The peak drag coefficient of 0.62 then occurs transonically, where the dynamic pressure is still small.
The Flight Test Record
There is no flight test record. No flight of the X-60A is recorded [Directory of U.S. Military Rockets and Missiles], and this section is an account of how far a programme can get without flying and of how the record of it ends.
What can be established from documents is a short list.
| Date | Event | Source |
|---|---|---|
| June 2014 | SBIR Phase I awarded | [USAspending] |
| July 2015 | Phase II awarded | [USAspending] |
| by December 2017 | three captive-carry flights of full-scale inert vehicles completed | [Directory of U.S. Military Rockets and Missiles] |
| 27 March 2017 | flight-test contract signed | [USAspending] |
| 7 September 2018 | designation X-60A allocated | [Parsch, DOD 4120.15-L Addendum] |
| 4 October 2018 | designation announced | [Air Force] |
| 7 March 2019 | critical design review complete, first flight in about a year | [AFRL] |
| 14 January 2020 | integrated propulsion hot fire at Cecil Spaceport | [AFRL] |
| February 2020 | first flight deferred from March to later that year, no reason given | [Directory of U.S. Military Rockets and Missiles] |
| after February 2020 | nothing |
The programme reached its last reported milestone before flight and stopped there. The propulsion release of 15 January 2020 describes cold-flow and hot-fire testing with flight-like hardware and flight-like procedures, covering full-duration burns, engine gimballing for thrust vector control and system throttling [AFRL].
The programme manager’s words in that release are the last statement about a first flight in any of the three Air Force releases.
This test series was a critical step in reducing risk and gathering necessary system integration data in preparation for our upcoming flight tests. When we go to flight later this year, we hope to demonstrate the capability of the X-60A to provide affordable access to hypersonic flight conditions, which will position AFRL to deliver an innovative test capability for the Air Force and other DoD organizations.
The next month the flight moved and nothing further was published. The specialist registry that tracks these vehicles records the position plainly, that after February 2020 no further news items appear and that no solid information about a first flight, further delays or a cancellation is available [Directory of U.S. Military Rockets and Missiles].
The Contract Did Not Stop When the Publicity Did
The federal contract record continues for three more years and gives a different account of the same programme.
Contract FA865017C2414 ran from 2017-03-27 to 2023-02-28, a period of performance of 2,164 days, and carried 30 modifications [USAspending].
Two federal records describe that contract and they give different end dates. The small-business award record, which carries the contract number in its dashed form together with the solicitation topic AF141-081 and the solicitation year 2014, gives an award end date of 31 August 2022 [SBIR award 167092]. The contract record gives 2023-02-28.
The modification history reconciles them exactly, and the reconciliation matters, because a six-month discrepancy between two government databases usually means one of them is wrong. Neither is. 3 modifications fall after the award record’s end date, and the first of them, dated 9 November 2022, is a no-cost time extension. A no-cost extension is the instrument that moves an end date without moving any money. One record states the award as awarded and the other states it as extended.
The award record also carries the programme’s abstract, cut off in mid-word. It ends validate the f, an artefact of the database rather than of the programme, recorded here because a reader following the citation will see a sentence that stops. Of the 30,921,064.62 dollars obligated against it, 21,608,210.46 was obligated before February 2020 and 9,312,854.16 after. That is 30.1 percent of the money, across 11 actions, spent after the last thing the public was told.
The purchase descriptions are the story and they change. Every modification through 2019 names flight testing. The modification of 7 May 2020, three months after the deferral, obligates 4,808,000 dollars and is described as numerical analysis for scramjet and cold start. The money moved from flight to computation, and it did so in a line item.
What follows is an ending written in procurement language.
| Date | Modification | Obligation, dollars | Description |
|---|---|---|---|
| 2020-04-15 | P00019 | 1,000,000 | flight testing of an air launch testbed |
| 2020-05-07 | P00020 | 4,808,000 | numerical analysis for scramjet and cold start |
| 2021-05-03 | P00022 | 3,006,937 | flight test for an air launch test bed |
| 2021-08-18 | P00023 | −380,176 | flight test for an air launch test bed |
| 2022-11-09 | P00027 | 0 | no cost time extension |
| 2022-12-22 | P00029 | 22,873.11 | proposal to pay for shipping of equipment |
| 2023-06-22 | A00001 | −178,780 | closing action |
The last money the Air Force obligated on the X-60A contract was 22,873.11 dollars to ship the equipment somewhere. That is the final positive obligation on the contract, dated 2022-12-22, and its description is proposal to pay for shipping of equipment ncte.
The record therefore ends 1,237 days after it went quiet, or 3.39 years, and it ends with a deobligation. 2 negative actions returned 558,956.33 dollars and 6 modifications obligated nothing at all.
No cancellation notice has been found and this article does not claim one exists. What the documents support is narrower and stranger. A programme stopped being talked about in February 2020, kept being paid for another 3.07 years, spent a large fraction of that money on analysis rather than flight, and closed out by paying to move its hardware.
What the Programme Delivered, Counted
The figure of merit to apply is the one the programme itself invited with the wind tunnel comparison.
\[c_s \;=\; \frac{C_t}{N_f \, \tau} \tag{63}\]The denominator has two factors and one of them is known exactly.
\[c_s \;=\; \frac{30,921,064.62}{N_f \, \tau} \quad \text{with} \quad N_f = 0 \tag{64}\]The denominator’s other factor is a dwell, meaning the time a flight spends above the Mach number that counts as being at condition.
\[\tau \;=\; \int_{0}^{t_b} dt \;\; \text{over the interval where} \;\; M(t) \ge M_d \tag{65}\]0 flights were flown and 0 seconds of test condition were delivered. The cost per second of hypersonic condition supplied by the X-60A is not large. It is undefined.
The number the programme would have achieved can still be computed, and it should be, because the programme deserves to be measured against its ambition as well as its outcome. On the integrated trajectory, a vehicle carrying the Mach 6 propellant load spends 12.2 seconds above Mach 5, which is 13.9 percent of an 87.8 second burn. Against the 30,921,064.62 dollars obligated, a single flight would have cost 2,538,675 dollars per second at condition, four flights 634,669, and ten flights 253,868.
Those are development costs divided by flights, not marginal costs, and dividing a development programme by its first article always produces an absurd number. The two terms behave differently and the article keeps them apart.
\[\frac{C_t}{N_f} \;=\; \frac{C_t}{N_f} \bigg|_{\text{development}} + \; c_m \tag{66}\]The first term falls as the reciprocal of the flight count and the second does not fall at all, so an average cost per flight approaches the marginal cost from above and never reaches it. The honest reading is the third column. At ten flights the figure approaches a quarter of a million dollars per second of hypersonic condition, and whether that is cheap depends entirely on what a second of the same condition costs in a ground facility. The programme never got to make that comparison.
The Dwell Is the Uncomfortable Number
12.2 seconds is short, and it is short for a structural reason rather than a design failure. A rocket that is still burning is still accelerating, so it crosses Mach 5 near the end of its burn and reaches its peak Mach number at burnout. The time above any given Mach number is therefore the tail of the burn and not the burn.
\[\frac{\tau}{t_b} \;=\; \frac{12.2}{87.8} \;=\; 13.9\ \text{percent} \tag{67}\]The register’s phrase for what the vehicle does is at cruise flight conditions [Parsch, DOD 4120.15-L Addendum], and a cruise is a steady state. The next section asks whether one exists.
Can the Condition Be Held
The register says the X-60A tests at cruise flight conditions [Parsch, DOD 4120.15-L Addendum]. A cruise is a steady state, so the claim has an exact answer.
At constant speed the thrust must balance the drag plus the component of weight along the flight path.
\[F \;=\; D + W \sin\theta \tag{68}\]That is one equation in one unknown, so the flight path angle a cruise would require is not a choice.
\[\sin\theta \;=\; \frac{F - D}{W} \tag{69}\]The largest the weight term can be is the whole weight, which happens in a vertical climb, so the test has an answer that does not depend on the trajectory at all.
\[F \;>\; D + W \quad \Longrightarrow \quad \sin\theta > 1 \quad \Longrightarrow \quad \text{no steady state exists} \tag{70}\]At Mach 6 on the published dynamic pressure of 1,649 pounds per square foot, which is 23,652 metres, the drag on the derived frontal area is 3,842 newtons. The vehicle at burnout weighs 6,604 newtons. Drag plus full weight is 10,446 newtons and the engine at its rated sea-level thrust produces 22,241, which is 2.13 times as much. The flight path angle that would absorb the excess needs a sine of 2.79, and no angle has one.
Every dynamic pressure in the corridor gives the same outcome. The required sine is 3.19 at 500 pounds per square foot, 3.02 at a thousand, 2.79 at the published condition and 2.66 at two thousand. All four exceed 1, which is the largest a sine can be.
So the vehicle cannot cruise at full thrust. It can only cruise throttled, and the depth required is the finding. A throttle setting is the fraction of rated thrust the engine is asked for, and holding a speed means asking for exactly the drag.
\[\phi \;=\; \frac{D}{F} \bigg|_{\text{rated}} \tag{71}\]| Dynamic pressure | Altitude at Mach 6 | Drag | Throttle setting to hold speed |
|---|---|---|---|
| 500 lbf/ft² | 31,553 m | 262 lbf | 5.2 % |
| 1,000 lbf/ft² | 26,930 m | 523 lbf | 10.5 % |
| 1,650 lbf/ft² | 23,652 m | 864 lbf | 17.3 % |
| 2,000 lbf/ft² | 22,407 m | 1,047 lbf | 20.9 % |
A throttle range of 5.2 to 20.9 percent is at or beyond the edge of what liquid rocket engines have demonstrated. Deep throttling is difficult for a reason that can be written down. The pressure drop across an injector is what keeps the feed system from talking to the combustion chamber, and it follows the square of the flow rate through a fixed orifice area.
\[\Delta p_j \;=\; \frac{1}{2 \rho_b} \left( \frac{\dot{m}}{C_j A_j} \right)^2 \;\propto\; \dot{m}^2 \;\propto\; \phi^2 \tag{72}\]A throttle ratio therefore costs the square of itself in injector stiffness. At twenty percent thrust the drop is 4 percent of its rated value, at ten percent it is 1, and at five percent it is 0.25. An engine throttled far enough becomes unstable before it becomes quiet, and so deep throttling is an engine programme rather than a control setting [Sutton and Biblarz] [Huzel and Huang]. The deep throttling demonstrator derived from the RL10 for a lunar lander descent stage was built for that one requirement, and it reached a stable minimum of 5.9 percent of rated thrust only after its low-power combustion instabilities had been mitigated [Giuliano et al. 2010b].
This is why the Hadley has an active throttle, and the throttle is the strongest available evidence that the register’s word was chosen deliberately. An engine intended to accelerate a vehicle to a Mach number does not need to throttle at all. An engine intended to hold a vehicle at a condition needs to throttle very deeply indeed, and the propulsion release records that the ground campaign covered system throttling alongside full-duration burns and gimballing [AFRL].
Whether the Hadley reaches the depth the table demands is not published, and this article does not know. What it can say is that the top row of the table lies below the 5.9 percent that demonstrator reached and the bottom row is within the range of engines built to throttle deeply, and that the register’s phrase therefore describes an ambition at the boundary of the possible rather than a routine mode of operation.
The Corridor Is a Choice and Not a Limit
A compensating result follows, and it matters more.
Flying the integrated ascent on 53 pitch programmes, with the same vehicle and the same propellant load, the dynamic pressure at which the vehicle first reaches Mach 5 ranges from 54 to 3,928 pounds per square foot. That is a factor of 72.8.
\[\frac{q_{\max}}{q_{\min}} \bigg|_{M \ge 5} \;=\; 72.8 \tag{73}\]The altitude at which it happens ranges from 55.7 thousand feet to 147.9 thousand feet.
Dynamic pressure is a property of the trajectory and not of the vehicle. The published pair of Mach 5 and seventy thousand feet sits unremarkably inside that range, and so does most of the air-breathing test corridor. That range makes a rocket with almost no wing a plausible substitute for a wind tunnel. A tunnel’s condition is fixed by its nozzle and its reservoir and changing it means changing hardware. This vehicle’s condition is fixed by its pitch programme, and changing it means changing a table in a flight computer.
Aircraft to the Register, Rocket to the Statute
The X-60A’s designation is X-60A, which is an aircraft designator. This section establishes that from the governing instruction rather than by inspection, because the point is not that somebody chose the wrong words.
There Are Two Designation Systems and the X Means Different Things in Them
Department of the Air Force Instruction 16-401 governs the designation of American military aerospace vehicles [DAFI 16-401]. It defines the standardised symbol set as applying to vehicles categorised as aircraft, guided missiles, rockets, probes, boosters, and satellites, and it then splits that list into two designator systems with different grammars.
The designator itself is what the instruction calls a Mission Design Series, abbreviated MDS, and the two grammars differ in which symbols they require.
Standard aircraft MDS designators are comprised of the following: status prefix (optional), modified mission (optional), basic mission (required), design number (required), design series (required).
Guided missiles, rockets, probes, boosters, and satellite MDS designators are comprised of the following: status prefix (optional), launch environment (required), basic mission (required), design number (required), design series (required).
In the aircraft system the letter X appears twice, in two different columns. As a status prefix it means Experimental, defined as Aircraft in a developmental or experimental stage. As a basic mission it means Research, defined as Aircraft designed for testing highly experimental configurations. These aircraft are not generally intended for use as operational aircraft.
In the missile, rocket, probe, booster and satellite system the letter X appears once, and only as a status prefix, defined as Vehicle in a development or experimental stage. That system has no Research basic mission at all. Its basic missions are transport, surface attack, aerial and space intercept, decoy, drone, launch detection, navigation, scientific and calibration, space support, training, underwater attack, weather, and electronic or communications.
The consequence is structural, and this article exists because of it.
A vehicle designated under the rocket system cannot be an X-plane. Its designator would open with a launch environment symbol, which for an air-launched vehicle is A, and it would carry a vehicle type symbol, which for a rocket is R and for a probe is N. It would look like the register’s other rockets and not like an X number. The X in X-60A is not the experimental status prefix. It is the Research basic mission, and the Research basic mission is defined over aircraft.
So the register calls the X-60A an aircraft because the only door into the X series is the aircraft door. The word is not an error. It is a consequence of the taxonomy, and the taxonomy has no category for a research rocket.
The Register Can Say Rocket and Chose Not To, Then Chose To
The entry reads in full as follows.
GOLauncher 1; This aircraft is an autonomous hypersonic vehicle that is capable of flight testing experimental hypersonic technologies at cruise flight conditions.
The register says nothing about the X-60A being a rocket. Its entry contains 0 occurrences of the word across 164 characters, while calling the subject an aircraft 1 time and a vehicle 1 time in the same sentence [Parsch, DOD 4120.15-L Addendum].
That is not a limitation of the register’s vocabulary. 3 of the 31 X rows name a rocket, being the X-40B, X-63A and X-64A. The X-63A and X-64A entries, allocated 20 April 2022, both carry 1 rocket engine in the engines cell and both describe a demonstrator rocket in their mission statement [Parsch, DOD 4120.15-L Addendum]. The register found the word about three and a half years after this allocation and about a designation that is unambiguously the same kind of thing.
The X-60A’s engines cell is empty. That means nothing on its own. 94 of the register’s 539 rows have no engine listed, among them the X-57 and the X-59, which are the two rows on either side of this one [Parsch, DOD 4120.15-L Addendum]. Three consecutive X allocations have an empty engines cell and all three vehicles have engines.
The Statute Asks a Question That Has a Number for an Answer
Where the designation system asks what to call the vehicle, federal law asks a question that can be computed.
The Commercial Space Launch Act defines a launch vehicle as a vehicle built to operate in or place a payload in outer space, or a suborbital rocket, and it defines the second of those precisely [51 U.S.C. 50902].
“suborbital rocket” means a vehicle, rocket-propelled in whole or in part, intended for flight on a suborbital trajectory, and the thrust of which is greater than its lift for the majority of the rocket-powered portion of its ascent.
That last clause is an inequality between two forces, evaluated over time. It is not a matter of nomenclature, of appearance or of intent. It is a test.
\[F \;>\; L \qquad \text{for the majority of } \; 0 \le t \le t_b \tag{74}\]Because the vehicle’s lift coefficient is unpublished, this article does not guess it. The integration solves for the lift the commanded pitch programme requires at each instant, and compares that to the thrust.
\[n \;=\; \frac{L}{W}, \qquad F > L \quad \Longleftrightarrow \quad n < \frac{F}{W} \;=\; 1.668 \tag{75}\]Across all 53 pitch programmes, thrust exceeds lift for 100 percent of powered ascent in the worst case. The largest lift demanded anywhere in the set is 0.591 of the thrust. The statute’s threshold is a majority, and the set is unanimous.
The Definition’s Second Half Is Also Computable
The thrust-against-lift clause is not the whole test. A suborbital rocket must also be intended for flight on a suborbital trajectory, and the statute defines that term too [51 U.S.C. 50902].
“suborbital trajectory” means the intentional flight path of a launch vehicle, reentry vehicle, or any portion thereof, whose vacuum instantaneous impact point does not leave the surface of the Earth.
A vacuum instantaneous impact point is where the vehicle would land if the engine stopped and the air vanished. Finding it is a two-body problem with a closed-form answer. The burnout state gives a specific energy and a specific angular momentum.
\[\varepsilon \;=\; \frac{V^2}{2} - \frac{\mu_E}{r_b}, \qquad \ell \;=\; r_b V \cos\theta \tag{76}\]Those two fix the coasting ellipse completely.
\[a_s \;=\; -\, \frac{\mu_E}{2 \varepsilon}, \qquad e_c \;=\; \sqrt{ 1 + \frac{2 \varepsilon \ell^2}{\mu_E^2} }, \qquad r_p \;=\; a_s \left( 1 - e_c \right) \tag{77}\]And the ellipse either reaches the surface or it does not.
\[r_p \;<\; R_m \quad \Longleftrightarrow \quad \text{the vacuum instantaneous impact point does not leave the surface} \tag{78}\]On the integrated trajectory the vehicle burns out at 1,805.9 metres per second and 24,209 metres. The resulting ellipse has a semi-major axis of 0.515 Earth radii and an eccentricity of 0.9477, giving a perigee radius of 171,811 metres, which is about 6,199 kilometres below the surface. The impact point is not merely on the Earth. It is deep inside it.
The same state read against orbital speed says how far from orbit the vehicle is.
\[V_c \;=\; \sqrt{\frac{\mu_E}{r_b}}, \qquad \frac{V}{V_c} \;=\; 22.9\ \text{percent} \tag{79}\]Burnout speed is 22.9 percent of circular orbital speed at that altitude and 5.2 percent of the kinetic energy. Those ratios quantify the observation that an endoatmospheric testbed and a launch vehicle are not the same kind of machine even though both are rockets. Both halves of the statutory definition are satisfied, and neither was satisfied by assertion.
The X-60A is a suborbital rocket in the sense that matters legally and an aircraft in the sense that matters bureaucratically, and the two systems were never designed to agree because they were written for different purposes by different bodies.
Which Regime Would Have Governed the Flight Is Genuinely Unclear
The programme chose a commercial spaceport on purpose and said so.
A key part of the X-60A program is that the U.S. Federal Aviation Administration-licensed Cecil Spaceport provides a diversification in hypersonic flight testing to traditional Department of Defense flight test ranges.
The critical design review release makes that point [AFRL], and the designation release adds that the vehicle would use new space commercial development, licensing, and operations practices [Air Force]. Licensing is named explicitly, and the licence a spaceport holds is a Federal Aviation Administration licence to operate a launch site and not an airworthiness certificate [14 CFR Part 420].
The regulations carry the statute’s definitions forward. Section 401.7 of Title 14 of the Code of Federal Regulations, cited as 14 CFR 401.7, defines a launch vehicle and a suborbital rocket in the same terms the statute uses [14 CFR 401.7] [14 CFR Part 401], and the licensing requirements themselves were consolidated into Part 450 by a final rule published on 10 December 2020 [85 FR 79566] [14 CFR Part 450]. That rule postdates the X-60A’s planned first flight by nine months, so a vehicle flying in March 2020 would have been licensed under the predecessor parts, and one flying in 2023 could have been licensed under either, because the rule took effect in March 2021 and kept the predecessor parts in force for five years after that [85 FR 79566]. The programme spanned the change.
But the statute contains an exemption that may swallow the case. The chapter does not apply to a launch, reentry, operation of a launch vehicle or reentry vehicle, operation of a launch site or reentry site, or other space activity the Government carries out for the Government [51 U.S.C. 50919]. Whether the Air Force Research Laboratory buying flights from a contractor, flown from a commercially licensed spaceport, is the Government carrying out an activity for the Government is a question this article cannot resolve and has found no document resolving.
What can be said is that the vehicle sat on the seam. It held an aircraft designation, satisfied the statutory definition of a suborbital rocket, and was to fly from a site licensed under a regime whose applicability to it was arguable. The specialist registry resolved the same question by filing the X-60A in the Directory of U.S. Military Rockets and Missiles rather than among the aircraft [Directory of U.S. Military Rockets and Missiles], which is a third answer from a fourth authority.
The Crewing Symbol That Was Not Used
One more symbol is missing. The same gap, seen from the other side, cost the X series the number 58.
The aircraft designator system has a vehicle type column, required on a non-standard aircraft designator, in which Q means Unmanned Aircraft [DAFI 16-401]. The register’s statement calls the X-60A autonomous. It carries no Q.
Nor does any other X row. 12 of the 31 X rows describe an uncrewed vehicle in their mission statement, being the X-45A, X-45B, X-45C, X-46A, X-47A, X-48A, X-48B, X-48C, X-56A, X-60A, X-65A and X-76A, and 0 of the 31 carry the Q symbol. Meanwhile 69 rows elsewhere in the register do carry it, including the XQ-58A allocated 424 days before this one [Parsch, DOD 4120.15-L Addendum].
The rule the register actually follows is that the X series designates by role and not by crewing. A research vehicle takes X and a number whether or not anyone is aboard, and a drone takes the Q. The X-58 article found that this convention cost the X series a number. This article finds the same convention operating in the other direction, letting an uncrewed rocket into a series defined over aircraft without any symbol recording either fact.
Comparison With Ground Prediction
There is no flight result to set beside any ground prediction, because the X-60A never flew. The earlier count of what the programme delivered establishes that 0 flights were flown and 0 seconds of test condition were delivered. Every prediction made for the vehicle on the ground therefore stands unchecked by the measurement it was made to be checked against, and this section records what those predictions were so that the absence has a definite shape.
The programme’s own predictions were a condition and a date. The designation release promised access to high dynamic pressure conditions between Mach 5 and Mach 8 [Air Force, 4 October 2018], and the specialist directory’s specification table gives a ceiling of more than 21,300 metres [Directory of U.S. Military Rockets and Missiles]. The critical design review release of 7 March 2019 expected a first flight in about a year [AFRL], and the propulsion release of 15 January 2020 expected flight later that year [AFRL]. The date was not met and the condition was never attempted. In February 2020 the first flight was deferred without a stated reason, and nothing further was published [Directory of U.S. Military Rockets and Missiles].
The ground campaign returned results, and they are ground results. Three captive-carry flights of full-scale inert vehicles were complete by December 2017 [Directory of U.S. Military Rockets and Missiles], and an inert vehicle carried under an aeroplane is not a powered flight. The integrated propulsion tests at Cecil Spaceport covered full-duration burns, gimballing for thrust vector control and system throttling with flight-like hardware [AFRL]. The record cited here publishes no measured figure from either campaign, so not even a ground measurement is available to set beside the estimates this article makes.
This article’s own figures are predictions of the same kind, and none has a flight value beside it. The sizing from first principles reads the published Mach number and ceiling as a dynamic pressure of 1,649 pounds per square foot. The analysis of dependent systems integrates an ascent on an assumed specific impulse of 290 seconds and a generic drag coefficient, and the account of the flight test record derives from that ascent a dwell of 12.2 seconds above Mach 5. The cruise analysis finds that a cruise at the condition would need a throttle setting between 5.2 and 20.9 percent of rated thrust, and records that whether the Hadley reaches that depth is not published. Each of those is a ground prediction with no flight to test it, and for that reason the discussion of where the framing breaks down asks that the figures be read as order-of-magnitude statements with their assumptions attached.
The only comparison this article can make is between one prediction and another. The programme published Mach 5 at seventy thousand feet, and across 53 pitch programmes the integrated ascent in this article first reaches Mach 5 anywhere between 55.7 and 147.9 thousand feet, with the published pair inside that range. The two predictions are consistent, and their agreement says nothing about what the vehicle would have done.
The engine later flew, and that flight does not close the gap. The Hadley first flew on 9 March 2024 powering the Talon-A1 [Ursa Major], on a different airframe and without an X number. This article reports no thrust, specific impulse or throttle figure from that flight, so the assumed specific impulse and the throttle depth on which its X-60A figures rest remain unchecked.
The comparison the programme existed to make was never made either. Its stated purpose was to complement ground test facilities by testing technologies in actual hypersonic flight conditions [Hellman, AFRL], and the figure of merit that purpose implies, dollars per second of test condition, has a denominator of zero. Whether a second of flight condition would have been cheaper than the same second in a ground facility remains unanswered, as the cost analysis above observes.
What the Data Changed
An aeroplane that produced no data changed nothing by measurement, and saying so is the finding rather than an omission. The same holds for the X-39 and the X-54. The X-60A is a third case and a different one, because unlike either of those it was built.
Three things did change, and each is documented.
The designation route changed. The Air Force’s claim that this was the first of its small-business programmes to hold an X number is a claim about eligibility [Air Force]. Whatever happened to the vehicle, the precedent stands, and the X-63A and X-64A followed in 2022, allocated to ABL Space Systems and to a three-company team as demonstrator rockets for an Air Force Research Laboratory programme [Parsch, DOD 4120.15-L Addendum].
The engine changed hands and flew. The Hadley was first qualified in 2021, a year after the X-60A’s planned first flight [Ursa Major]. Its hypersonic variant was developed with Stratolaunch, and the engine made its first flight on 9 March 2024 powering the Talon-A1 testbed [Ursa Major] [Stratolaunch Talon-A]. That vehicle had described itself in the same conference series and almost the same words, as an air-launched hypersonic testbed, in a paper given three years after the X-60A paper [Corda et al. 2018] [Piplica et al. 2015]. The engine’s first flight came 1,469 days after the start of March 2020, the month in which the X-60A was to have flown, or 4.02 years, on somebody else’s airframe and without an X number.
And a general reference work on the X series ends at this vehicle. The specialist registry lists as the first of its sources a 2021 volume titled X-Planes from the X-1 to the X-60 [Directory of U.S. Military Rockets and Missiles]. The title is a fact about a publication date and not a judgement about the series, since the X-61 had been allocated two years earlier [Parsch, DOD 4120.15-L Addendum].
The requirement did not go away either. The parent company’s site lists both the X-60A and an X-60C among past projects [Directory of U.S. Military Rockets and Missiles]. No X-60C appears anywhere in the register, which has exactly 1 row whose designation begins X-60 [Parsch, DOD 4120.15-L Addendum]. A successor that carries the number without the paperwork is the mirror image of a predecessor that carried the paperwork without the flight.
The Contemporary Literature
9,694 research records map the field this vehicle sits in, across 20 clusters. Every row states its count, and the counts sum to the total exactly.
| Cluster | Records |
|---|---|
| The vehicle, the programme and the vehicles it is measured against | 448 |
| Sounding rockets and suborbital research vehicles | 170 |
| Getting it off the wing, which is where the trajectory starts | 271 |
| Launch vehicles, which set the ratios this vehicle is measured against | 549 |
| The corridor, and the trajectory that has to stay inside it | 710 |
| The engine, which is the only part of the vehicle that is not a structure | 1,811 |
| Solid and hybrid rocket motors | 77 |
| What rides in the nose, which is why the corridor has to be held | 1,036 |
| Surviving the heat, which is a materials problem before it is a flow problem | 576 |
| Aerothermodynamics, which is what the corridor does to whatever is in it | 1,319 |
| Making hypersonic conditions on the ground, and why that is not enough | 651 |
| Measuring a flight that lasts a minute | 267 |
| Flight research programmes and the practice of flight test | 39 |
| Range safety, licensing and the rules a rocket flies under | 379 |
| What a flight test costs, which is the programme’s stated reason for existing | 206 |
| Flying a slender finned body, and holding it together | 597 |
| Guiding and controlling a hypersonic or entry vehicle | 230 |
| Hypersonic, glide and entry vehicles as designs | 172 |
| Hypersonic research programmes, reviews and histories | 45 |
| The atmosphere and the flight condition | 141 |
| Total | 9,694 |
The vehicle, the programme and the vehicles it is measured against
This is the cluster that names things. Two records name the X-60A’s own testbed, and the rest are the vehicles it is measured against, being the X-15, the Pegasus booster, the Aerobee and Black Brant sounding rocket families, the waverider research vehicles and the air-breathing flight experiments from HyShot and HIFiRE to the X-43 and the X-51.
448 records. [Adamczak et al. 2009] [Adamczak and Bolender 2015] [Adamczak et al. 2011] [Aerodynamic and Landing Measurements 1960] [Ahuja et al. 2026] [Akcal et al. 2017] [Alba et al. 2008] [Anderson and Fike 1969] [Arjun 2010] [Bahm et al. 2005] [Baird and Bergman 1970] [Banerjee et al. 2014] [Banner and Kinsler 1961] [Banner et al. 1962] [Banner and Kuhl 1965] [Barth and Eggers] [Barth and Longo 2010] [Bartolome Calvo and Eggers 2011] [Baumann 2006] [Baumann et al. 2008a] [Baumann et al. 2010] [Baumann et al. 2007] [Baumann et al. 2008b] [Berger et al. 2008] [Berger et al. 2009] [Bergman 1970] [Bertelrud et al. 2000a] [Bertelrud et al. 1992] [Bertelrud et al. 2000b] [Biella et al. 2022] [Black Brant XII 1999] [Black Brant-Rocket AMF-2-116 Launched 1968] [Blankson 1994] [Blankson et al. 1998] [Blocker and Ruebush 2005] [Bode et al. 2013] [Boehrk 2014] [Boehrk et al. 2012] [Bolender et al. 2015] [Bolender et al. 2012] [Borg et al. 2025a] [Borg et al. 2011] [Borg et al. 2012] [Borg et al. 2013] [Borg and Kimmel 2017] [Borg and Kimmel 2018] [Boyce et al. 2003b] [Boyce and Paull 2001] [Brown and Barhorst 2011] [Brown et al. 2011] [Brown and Boyce 2012] [Brown et al. 2012] [Burrows et al. 2024] [Burt 1975] [Bushnell et al. 1965] [Bushnell and Busse 1967] [Bushnell et al. 1967] [Busse 1967] [Busse and Kraft 1966] [Busse and Leffler 1966] [Bynum and Baurle 2011] [Cain and Walton 2003] [Candler et al. 2009] [Carandente and Scigliano 2016] [Carriage and Launch Characteristics 1994] [Cecere et al. 2010] [Chen and Zhao 2017] [Chen and Zhao 2019b] [Chou et al. 1996] [Choudhari et al. 2009] [Choudhury and Neely 2012] [Chuvakhov and Fedorov 2026] [Coble and Nagy 1964] [Cockrell et al. 2000a] [Cockrell et al. 2000b] [Coleman 2003] [Constantine et al. 2015] [Constantine et al. 2011] [Couture et al. 2008] [Creagh et al. 2012b] [Creagh et al. 2012a] [Cristillo et al. 2019] [Crow et al. 2012] [Cuda and Hass 2010] [Curry et al. 1992] [da Costa et al. 2016b] [da Costa et al. 2016a] [Dadd et al. 2006] [Dana 1987] [Dasgupta et al. 2012] [Glass et al] [Davis and White 2006] [Defoort et al. 2011] [Deora et al. 2023] [Di Benedetto et al. 2021] [Di Martino et al. 2026] [Ding et al. 2018] [Dolvin 2008] [Dungan et al. 2026] [Eggers and Barth 2006] [Eggers et al. 2005] [Eggers et al. 2006] [Eggers et al. 2009] [Elias and Knutson 1995] [Ellsworth 2010] [Emory et al. 2011] [Engelund 2001] [Engelund et al. 1999] [Eshtairy et al. 2025] [Ettl and Turner 2014] [Falempin et al. 2009a] [Falempin and Serre 2006] [Falempin and Serre 2008] [Favaloro et al. 2015] [Ferguson et al. 2015] [Ferlemann 2008] [Ferragut 1976] [Ferreira de Moura and Borges Ribeiro 2025a] [Ferreira de Moura and Borges Ribeiro 2025c] [Ferreira de Moura and Borges Ribeiro 2025b] [Ferreira de Moura and Borges Ribeiro 2025d] [Finch and Matranga 1959] [Finley and Cockrell 1995] [Fischbach 2014] [Flynn and Groves 1964] [Fortney 1965] [Franze 2016b] [Franze 2016a] [Franze 2026] [Frost] [Fureby et al. 2011] [Furudate et al. 2005] [Gardi et al. 2015] [Gardner] [Gardner et al. 2005] [Gardner et al. 2004] [Georgiadis et al. 2014] [Gibson et al. 2002] [Gillum et al. 1994] [Glass et al. 2014] [Piplica et al. 2015] [Gong et al. 1993] [Gong Weijie and Tang Shuo 2010] [Goodman and Ireland 2006] [Goodman and Ireland 2007] [Goodwin and Maxwell 2017] [Gosse et al. 2010] [Grindle 2011] [Grindle and Bahm 2006] [Gruber et al. 2009] [Guelhan et al. 2026] [Guelhan et al. 2012] [Gülhan et al. 2023] [Gülhan et al. 2024] [Gupta et al. 2001] [Haney 1995] [Haney et al. 1993] [Hank et al. 2008] [Hannemann et al. 2009] [Hansen et al. 1967] [Hass et al. 2011] [Hass et al. 2005b] [Hass et al. 2010] [Hass et al. 2005a] [He 2015] [Hegedus and Mendenhall 2003] [Hemanth et al. 2009] [Hembling et al. 2021] [Hewes et al. 1958] [Ho 2006] [Hoey 1991] [Hoidale 1963] [Holland et al. 2000] [Howard] [Huebner et al. 2001b] [Noubel and Lago 2021] [Iaccarino et al. 2010] [Ingenito et al. 2010] [Isaac and Miles 1990] [Jackson et al. 2009] [Jackson et al. 2011b] [Jackson et al. 2013] [Jackson et al. 2015] [Jackson et al. 2011a] [Jade et al. 2025] [Javaid and Serghides 2004] [Lux-Baumann and Burkes 2005] [Jewell et al. 2017b] [Jewell et al. 2015] [Jewell et al. 2017a] [Johnson 1994] [Johnson et al. 2007a] [Jones and Tharayil 1982] [Jones 2006] [Joseph et al. 2026a] [Joyce et al. 2005] [Juliano et al. 2014] [Juliano et al. 2015b] [Juliano et al. 2015a] [Kacpura and Acevedo 1998] [Kanderpalli et al. 2014] [Karl et al. 2006] [Karl et al. 2008] [Karl et al. 2012a] [Karl et al. 2011] [Kennell et al. 2016] [Kim et al. 1982] [Kimmel 2008] [Kimmel et al. 2007] [Kimmel et al. 2010] [Kimmel et al. 2011] [Kimmel et al. 2013] [Kimmel et al. 2014] [Kimmel et al. 2017] [Kimmel et al. 2018b] [Kimmel et al. 2018a] [Kimmel et al. 2015] [Kimmel and Prabhu 2015] [Kinsler 1958] [Kitt Peak National Observatory 1972] [Kocian et al. 2017] [Kodera et al. 2005] [Ladeinde 2019] [Lane and Chalfant 1967] [Lane et al. 1982] [Lane and Redman 1970] [Langener et al. 2012] [Larsson 2012] [Lau et al. 2012] [Laurence et al. 2015] [Leng et al. 2024] [Leng et al. 2025b] [Lewis 1991] [Li et al. 2014] [Li et al. 2011d] [Li et al. 2015g] [Lien et al. 2004] [Li et al. 2012b] [Li et al. 2012c] [Lin and Shen 1997] [Lindberg 1989] [Liu and Gruber 2011] [Liu et al. 2005a] [Ljunge and Hall 1982] [Ljunge and Hall 1984] [Loehle et al. 2012] [Longo 2008] [Lorenz and Bierig 2013] [Lux-Baumann and Burkes 2006] [MacLean et al. 2008] [Malik et al. 2007] [Marini et al. 2017] [Marshall et al. 2005b] [Marshall et al. 2005a] [Martineau et al. 1990] [Martinez Schramm et al. 2015] [Martinez Schramm et al. 2008] [Martinez Schramm et al. 2009] [Matranga 1961] [Matranga et al. 1962] [Matthews and Jones 2005] [McClinton 2006] [McClinton et al. 2001] [Mechanical Architecture and Status 2004] [Choudhari and Li] [Choudhari et al. 2020] [Melander and Candler 2024] [Melander et al. 2020] [Mendenhall et al. 1997] [Meyer et al. 1992] [Missiles Rocketry 2011] [Mohring et al. 2021] [Molvik et al. 1993a] [Molvik et al. 1993b] [Montag et al. 1982] [Montag and Walker 1979] [Moran et al. 2023] [Morelli et al. 2005] [Mosier et al. 1991a] [Mosier et al. 1991b] [Moyes et al. 2017] [Moyes et al. 2018] [Murphy and Agarwal 2022] [Murray and Steelant 2009] [Musa et al. 2024] [Neel et al. 2017] [Neel et al. 2018a] [Neel et al. 2018b] [Neely et al. 2011] [Neuenhahn et al. 2006] [Noffz and Curry 1991] [Noffz et al. 1991] [Noffz et al. 1992] [Nordin-Bates and Fureby 2015] [Nordin-Bates et al. 2017] [Numerical Research of Three-Dimensional 2008] [Odam et al. 2009] [Ohlhorst et al. 2005] [O’Neill and Lewis 1992] [O’Neill and Lewis 1993] [Osterholt and Kelly 2020] [Paredes and Theofilis 2015] [Park et al. 2025] [Paull et al. 2005] [Payne and Mayo 1979b] [Payne and Mayo 1979a] [Pecnik et al. 2012] [Peebles 2008] [Peebles 2007] [Pegasus 1988] [Petersen et al. 1962] [Pezzella et al. 2014] [Ping Li et al. 2010] [Pisano and Whitfield 2024] [Porter et al. 2017] [Prime et al. 2012] [Püttmann et al. 2005] [Püttmann and Longo 2006] [Quintanilha Junior et al. 2019] [Rana et al. 2009] [Rana et al. 2011] [Rault 1992a] [Rausch et al. 2000] [Raz et al. 2026] [Razzaqi et al. 2018] [Reed and Watts 1961] [Reimer et al. 2025] [Research-Airplane-Committee Report on Conference 1958] [Reubush et al. 2003] [Rhode et al. 1995] [Richman 1967] [Quinn and Olinger 1969] [Roberts et al. 2012] [Robinson and Martin 2006] [Rodi 2012] [Rodi 2020] [Rodi 2021] [Rogers 1963] [Rogers et al. 2005a] [Rovner 1991] [Sagliano et al. 2014] [Sanderson 1965] [Santos 2011] [Santos 2012] [Sappey et al. 2009] [Sarosh 2021] [Schade and Mosier 1994] [Schettino et al. 2020] [Scigliano et al. 2015] [Scigliano et al. 2017] [Seleznev 2021] [Serre and Defoort 2009] [Sevier et al. 1976] [Sharifzadeh et al. 2012] [Sharifzadeh et al. 2014] [Shi et al. 2023] [Shirouzu and Watanabe 1993] [Shvets et al. 2005] [Siewert et al. 1995] [Smart et al. 2006] [Smart and Suraweera 2009] [Smelt 1959] [Smith et al. 2011] [Spivey et al. 2018] [Stanfield et al. 2012b] [Stanfield et al. 2012a] [Stanfield and Kimmel 2013] [Starkey et al. 2005] [Steelant 2006] [Steelant 2008] [Steelant 2009] [Steelant 2011] [Steelant et al. 2015b] [Steelant and van Duijn 2011] [Steelant et al. 2015a] [Steeves et al. 1973] [Storch et al. 2011] [Corda et al. 2018] [Sunami et al. 2006] [Surzhikov 2020] [Takashima et al. 1996] [Tarpley and Lewis 1995] [West and Bynum] [West et al] [Tincher and Burnett 1992] [Tirtey et al. 2011] [Tirtey et al. 2012] [Tough 1967] [Tremant 1962] [Tufts et al. 2018a] [Tufts et al. 2017] [Tufts et al. 2018b] [TÜRkoĞLu et al. 2026] [Turner et al. 2006] [ul Islam Rizvi et al 2015] [Underwood 1986] [Vishesh and Sivasubramanian 2023] [Van Allen et al. 1948] [van Brummen et al. 2015] [Vincent-Randonnier et al. 2014] [Voevodenko et al. 2015] [Voland et al. 2006] [Voland et al. 2005] [Wadhams et al. 2008b] [Wadhams et al. 2008c] [Wadhams et al. 2008a] [Walker and Rodgers 2005] [Walker et al. 2008c] [Walker et al. 2008a] [Walker et al. 2008b] [Walker and Wolowicz 1962] [Walker 1962] [Ward and Smart 2026] [Wartemann et al. 2016] [Watanabe et al. 1996] [Watanabe et al. 1997a] [Watanabe et al. 1997b] [Weihs et al. 2008] [Weihs et al. 2006] [Weirs 2019] [Wen et al. 2011] [West and Bynum 2021] [West and Bynum 2024] [West et al. 2026] [Dana 1993] [Wilson Chan et al. 2014] [Won et al. 2006] [Won et al. 2010] [Wu and Xiao 2009] [Wylie and McGilvray 2019] [X-43A Research Vehicle Design 2011] [Xiao et al. 2006] [Xiaoqing et al. 2010] [Xing et al. 2017] [Xing et al. 2012] [Xuzhao et al. 2012] [Yancey 1964] [Yankui et al. 2005] [Yentsch and Gaitonde 2012] [Yentsch et al. 2014] [You and Liang 2009c] [You and Liang 2009a] [You and Liang 2009b] [You et al. 2009] [Zettervall et al. 2015] [Zhao et al. 2022a] [Zheng et al. 2020b] [Zubin et al. 1997]
Sounding rockets and suborbital research vehicles
Sounding rockets as vehicles rather than as platforms for the science they carry, being their design, motors, attitude control, recovery, ranges, launch campaigns and programmes, because a sounding rocket is this vehicle’s direct ancestor and the vehicle it was built to do the opposite of.
170 records. [A French Meteorological Rocket 2004] [Abbott and Walker 1970] [Alford et al. 1982] [Alford et al. 1972] [Alford and Hoekstra 1976] [Ammons 1973] [Ammons et al. 1970a] [Ammons et al. 1970b] [An Improved Theoretical Aerodynamic 1979] [Armen 2010] [Arritt et al. 1973] [Arves et al. 2003] [Asanuma and Nomura 1976] [Atkinson et al. 2007] [Atwood and Soss 1976] [Baber 1967] [Rifà et al. 2022] [Banks 1992] [Baran et al. 2015] [Basciano 1998] [Boersma et al. 1970] [Bollermann and Wright 1973] [Bollermann and Walker 1968] [Bolster 1967] [Boscov 1982] [Braswell et al. 2017] [Briggs et al. 1970] [Brooks et al. 2010] [Brown 1960] [Brunk 1966] [Brunk 1967] [Bull and Murphy 1967] [Bumgarner and Gilcrease 1979] [Cassell et al. 2019b] [Cassell et al. 2019a] [Ceresuela 1967] [Chelstowski et al. 2018] [Cho et al. 2008] [Chown et al. 1970] [Churchyard 1979] [Clarke 1998a] [Clarke 1998b] [Conrad and Modlin 1965] [Cooper and Seaton 1982] [Crough and Gallow 1966] [Curry and Uselton 1967] [Dąbrowski and Krawczuk 2021] [Dembrow and Jamieson 1964] [De Pauw et al. 1968] [Do et al. 2018] [Duncan and Engebos 1969] [Dunfee and Oss 1967a] [Dunfee and Oss 1967b] [Eberspeaker and Fairbrother 2013] [Eberspeaker and Smith 2003] [Esper et al. 2011] [Experimental Polish Meteorological Rocket 1959] [Ferragut and Rast 1986] [Flores and Gurkin 1982] [Flowers 1976] [Flowers and Needleman 1999] [Furst and Hazell 1970] [Garcia and da Silveira 2015] [Genevieve et al. 2012] [Geske-Wilson et al. 2026] [Goddard’s Rocket for Exploring 1924] [Graham 1965] [Greeb and Shrewsberry 1970] [Griner 1967] [Groteluschen 1967] [Guelhan 2017] [Gurkin 1992] [Harrington and Bullock 1962] [Hawks 1965] [Hazell et al. 1967] [Herbert 1967] [Herrick et al. 1990] [Hertz et al. 2021] [Howard 1970] [Hwang et al. 2006] [Ito et al. 2020] [Sterhardt 1965] [Jenkins 1970] [Jenkins et al. 1971] [Jenkins et al. 1973] [Jenkins et al. 1974] [Jones et al. 1957] [Jönsson 1988] [Jung and Serra 2005] [Karlgaard et al. 2018] [Karlgaard et al. 2019] [Kerstein 2003] [Kerstein et al. 2004] [Korzeniowski 2025] [Kozuma et al. 1983] [Kuzuu et al. 2011] [Lane and Mayo 1980] [Laudadio 1973] [Lin 1989a] [Liu 1959] [Lotz and Ference 1948] [Lydon and Va 1995] [MacLean] [Malina and Smith 1938] [Martín Canales Romero 2012] [Mayo 1967] [Mayo 1966] [McGarvey 1967] [McKee 1965] [McKenna 1990] [Millard 1970] [Miller 1969a] [Mogavero 1976] [Morrow and Pines 2000] [Murrow 1965] [Myung Brian Lee 2017] [Nolan 1967] [Okninski et al. 2015] [Olsen 1979] [Oss 1966] [Overmier 1967] [Owens and Riddle 1998] [Ozawa and Shimada 2017] [Papa and Azevedo 2003] [Patterson 1982] [Pepermans et al. 2018] [Pickell 1976] [Pillai 2018] [Polish Meteorological Rocket System 1969] [Price 1967] [Rasmussen and Chalfant 1979] [Rasmussen et al. 1967] [Rehri and Pennanech 1973] [Richards 1967] [Rismut and Bouties 1967] [Robbins and Zebrowski 1966] [Burth 2025] [Roehrig 1982] [Rosanova 2013] [Sanders et al. 2007] [Schaefer 1962] [Schneiders and Ziegltrum 1982] [Schüttauf 2017] [Shrewsberry 1973] [Silbert 1975] [Skoog 2006] [So 2026] [Stanfield 2026] [Stochastic Flight Simulation Applied 2004] [Strickland and Shigemoto 1979] [Sumanik] [Technical Engineering Services 1972] [The ARC AS Meteorological 1969] [The KOOKABURRA Meteorological Rocket 1969] [The PWN-8B Meteorological Rocket 1969] [The Skua Meteorological Rocket 1969] [Törnqvist et al. 2006] [Tsien and Evans 1951] [Tsien and Malina 2012] [Turner 1982] [Tynis et al. 2019] [Vickery 1963] [Villanueva 2018b] [Walker 1954] [Wercinski et al. 2017] [Wessling and Maybee 1989] [Wessling and Maybee 1991] [Windsor 1976] [Zetterquist 1979] [Zilliac 2012]
Getting it off the wing, which is where the trajectory starts
Air launch, which separates this vehicle from the ground-launched sounding rockets it descends from, although a series of air-launched sounding rockets was designed and tested in the 1960s [Bolster and Googins 1967]. Carriage loads, captive carry, release dynamics and the separation problem, plus the trade studies that ask whether launching from an aeroplane is worth the aeroplane.
271 records. [Ahn et al. 2024] [Ailneni et al. 2023] [Aircraft Store Separation Motion 1980] [Albertson et al. 2012] [ALE 1977] [Lee 2004a] [Arabshahi and Whitfield 1989] [Atwood 1995] [Atwood 1993] [Balachandran et al. 2023] [Basoglu et al. 2011] [Berglind and Tysell 2011] [Billingsley et al. 1979] [Binkley and Vanderwyst 2012] [Black 1968] [Black 1969] [Black and Picklesimer 1971] [Blades and Redgrave 2000] [Bolster and Googins 1967] [Boltz 2004] [Bordelon et al. 2003] [Breitsamter et al. 2001] [Brooks 1971] [Buchanan and Crosby 1983] [Bui et al. 2006] [Bui et al. 2007] [Buning et al. 2000] [Burton et al. 2007] [Campbell 2024] [Capel-Jorquera et al. 2025] [Capel-Jorquera et al. 2026] [Carlson et al. 1995] [Carman et al. 1980] [Addona et al] [Carter 2012a] [Carter and Lind 2012a] [Carter and Lind 2012b] [Cazier and Kehoe 1986] [Cenko 2025] [Chakravarthy and Szema 1991] [Chamberlain and Baltar 1993] [Ching 2000] [Choi et al. 2009] [Clapp et al. 2022] [Coleman et al. 1996] [Coley 2024] [Coogan and Musgrove 2017] [Winski et al] [Cross 1989] [Cui et al. 2021] [Cvrlje 1999] [Cvrlje and Laschka 2001] [Fanggidae and Kusumahardi 2025] [Daniels and Clare 1973] [Davids and Cenko 2001] [Deitchman 1957] [Demir 2018] [Demir and Alemdaroglu 2005] [Demory et al. 2011] [de Mûelenaere and Alonso 2018] [Depasquale et al. 2010] [Deslandes and Seifert 2000] [Di et al. 2013] [Dillenius et al. 1974] [Dillenius et al. 1975] [Disher 1954] [Donahue 2004] [Doolan 2006] [Doty 1983] [Doty 1985] [Du et al. 2026] [Duan et al. 2024] [Dudley and Torres 2007] [Edefur et al. 2007] [Elchert 1982] [Eramya et al. 2007] [Eramya et al. 2008] [Yoon 2009] [Fang et al. 2017] [Feaux et al. 1989] [Finney 2010] [Fokin et al. 2007] [Fulton 1977] [Gade and Inman 1999] [Gao et al. 2017] [Gaug et al. 2024] [Geisler et al. 2007] [Gill and Pace] [Goodwin et al. 1972] [Goodwin et al. 1971] [Gothard and Granlund 2022] [Grenoble et al. 2018] [Haglind et al. 2007] [Hallberg et al. 2008] [Hallberg et al. 2006] [Harding and Barton 2007] [Harish et al. 2006] [Heim 1991] [Hendrick and Saint-Mard 1999] [Hiwale et al. 2017] [Hoffren and Salminen 1999] [Horton 1964b] [Horton 1964a] [Hoyt 2006] [Huan-Ding et al. 2018] [Hudson 2005] [Jeyakumar et al. 2005] [Johnson et al. 2008b] [Jordan et al. 1997] [Kiber 1977] [Kim et al. 2005] [Kim et al. 2003] [Ko and Schuster 1983] [Kohiyar et al. 1992] [Kozak et al. 2013] [Kreeger et al. 1997] [Kumar et al. 2023] [Kumar et al. 1998] [Kwon et al. 2022] [Kwon et al. 2003] [Lee 2002] [Lee et al. 2011] [Lepore 2006] [Liao et al. 2023b] [Lijewski and Lijewski 1997] [Lijewski and Suhs 1992] [Lijewski and Suhs 1994] [Liu 2003] [Liu et al. 2020c] [Logan et al. 2006] [Logan et al. 2007] [Lottati 1988] [Loupy et al. 2018] [Lu et al. 2024] [Luo and Baysal 1999] [Luyten et al. 2025] [Lyu and Wang 2024] [Maddox 1980] [Madson et al. 1994] [Malmuth and Fedorov 2008] [Malmuth et al. 2005] [Mani et al] [Marcum 2001] [Matthews and Key 1977] [Matushin and Makhalov 2020] [Meakin 1992] [Miller et al. 2018] [Miura 2010] [Mizrahi and Raveh 2018] [Mizrahi and Raveh 2019] [Moog et al. 1979b] [Morgret et al. 2009] [Morris et al. 2011] [Moyer et al. 1995] [Murman et al. 2004] [Murray et al. 2009] [Naftel et al. 1986] [Nakahashi et al. 2002] [Nasiri et al. 2025] [Newman et al. 1992] [Newman and Baysal 1992] [Noh et al. 2007] [Kim 2005] [Oktay et al. 2008] [Baysal et al. 1989] [Olejnik and Zalewski 2020] [Olejnik et al. 2022a] [Omar et al. 2011] [Osman et al. 2015] [Pamadi et al. 2004] [Pamadi et al. 2009] [Pan et al. 2000] [Parikh et al. 1992] [Parikh et al. 1994] [Parkinson et al. 1995] [Peters et al. 2024] [Popa et al. 2016] [Poth et al. 1993] [Prananta et al. 2007] [Preisighe Viana et al. 2026] [Prilliman and Francis 1980] [Qian et al. 2017] [Quade 1978] [Rafique et al. 2011] [Rafique and LinShu 2009] [Rafique et al. 2009a] [Rafique et al. 2009b] [Rafique et al. 2009d] [Rafique et al. 2009e] [Rafique et al. 2009c] [Rafique et al. 2010a] [Rafique et al. 2010b] [Raharema et al. 2026] [Reed and Curry 1969] [Reed et al. 1980] [Reed et al. 1979] [Reubush 1999] [Reubush et al. 2001] [Rhee et al. 2008] [Richard and Putter 2003] [Rizk et al. 2002] [Rodighiero] [Roshanian and Talebi 2008] [Roychowdhury et al. 2019] [Runkle and Drobnik 1979] [Runkle and Woodis 1979] [Ryan 1966] [Saitoh et al. 2003] [Salt 2014] [Salt 2015] [Sanal Kumar et al. 2016] [Sarigul-Klijn and Sarigul-Klijn 2001] [Sarigul-Klijn et al. 2005] [Sarigul-Klijn et al. 2008] [Shankar and Malmuth 1980] [Shankar and Malmuth 1981] [Sikharulidze et al. 2005] [Singaravelu et al. 2009] [Singh et al. 2022b] [Snyder et al. 2010] [Snyder et al. 2003] [Sokolov 2016] [Song 2021] [Song et al. 2020b] [Sorensen and Blevins 2001] [Spahr 1974] [Spahr 1975] [Spahr and Sumlin 1974] [Spahr and Sumlin 1975] [Spinetti and Jolly 2008] [Stallings 1982] [Strutzenberg and Williams 2011] [尹 2023] [Sundaram and Wu 1983] [Tamer 2021] [Tarhan and Kavsaoglu 2005] [Thomas et al. 2007] [Thurston 1965] [Tomaro et al. 2000] [Toniolo et al. 2008] [Treece et al. 2024] [Tu et al. 1992] [Türk and Güleren 2025] [Unal and Baran 2018] [Unsteady Interaction Mechanism 2023] [Urbahs et al. 2021] [van den Broek 1984] [Verstraete et al. 2009] [Verstraete and Hendrick 2003] [Vishwajeet et al. 2025] [Wang 2015b] [Wang et al. 2022c] [Wang and Ma 2024] [Wang and Wang 1997] [Waskiewicz et al. 1981] [Webster and Bucy 1979] [Whitmore et al. 1994] [Woods et al. 2000a] [Xu and Tang 2010a] [Xue et al. 2019] [Xue et al. 2020] [Yan et al. 2025] [Yang et al. 2021] [Yin et al. 2024c] [Zaehringer et al. 2003] [Zhang et al. 2013] [Zhang et al. 2022c] [Zhang and Zhang 2020] [Zheng et al. 2013b] [Zheng and Zhang 2018] [Zhou et al. 2019a]
Launch vehicles, which set the ratios this vehicle is measured against
Launch vehicles as vehicles, being their design, sizing, staging, structures, recovery, reliability and operations, because the section headed Dependent Systems measures the X-60A against launch-vehicle thrust-to-weight ratios and stage structural coefficients, and the statute measures it against the definition of a launch vehicle.
549 records. [A Technical History 2022] [A Technology and Operations 1993] [Abrahamm and Valsa 2018] [Access to Space 2004] [Acharya and Sing 2000] [Adetoro et al. 2014] [Advanced Transportation System Studies 1995] [Aggarwal 2007] [Air Force Space Command Space Missile SYS CTR 2013] [Air Force Space Command Space Missile SYS CTR 2014] [Air Force Space Command Space Missile SYS CTR 2015] [Akimov 2026] [Allard 2024] [Allen 1964b] [Allen 2002] [Allen et al. 2000] [Allen et al. 1994] [Alp et al. 2023] [Alvord et al. 2024] [An and Li 2023] [Andrews 1998] [Andrews and Crocker 2004] [Antonenko and Belavskiy 2009] [Ariane Launch Vehicle 1977] [Astorg and Barreau, luiver, C 1995] [Atherton et al. 1999] [Bailey 2020] [Baldus et al. 2013] [Banerjee and Utreja 1975] [Barraza 1962] [Barreiro Treviño et al. 2026] [Barry et al. 1991] [Barth and Watson 2018] [Batenin et al. 2001] [Batts and Pearson 1996] [Batutina and Oliynik 2026] [Baumgartner 1997] [Baumgartner and Elvin 1995] [Bekey 1994] [Benton 1990] [Berglund 2003] [Berglund and Wilkins 2003] [Bermudez and Gladden 2003] [Bernstein et al. 1990] [Best et al. 2008] [Біляєв et al. 2024] [Bin 2017] [Blelloch et al. 2000] [Bliss et al. 2003] [Boliubash 2025] [Bolonkin 2002] [Braun et al. 1996] [Bremner 1992] [Pomeroy et al. 2024] [Breton et al. 2006] [Brevault et al. 2016] [Brevault et al. 2020] [Brice et al. 1966] [Brown and Littlefield 2010] [Brown and Olds 2005] [Buehrle et al. 2010] [Burkardt 1992] [Burrows and Roth 1992] [Buzuluk et al. 2020] [Buzzatto 2015] [Cai et al. 2024] [Caldwell et al. 2005] [Carson et al. 2015] [Carter et al. 1993] [Catania and Portanova 1996] [Chase 1979] [Chase 1980] [Chase 1992] [Chen et al. 1986] [Chiba et al. 2006] [Chiesa et al. 1999] [Childress-Thompson et al. 2017] [Claus and Zampino 2006] [Cockrell et al. 2006] [Cockrell et al. 2007] [Cockrell 2008] [Cockrell et al. 2009] [Coleman 2000] [Colicci et al. 2025] [Colonno and Alonso 2008] [Conger et al. 2002] [Cook 1995] [Cook 1996] [Cook and Vanhooser 2008] [Cook et al. 2009] [Corbet] [Curlander and Kiefer 1965] [Cusick and Kontis 2019] [Cusick et al. 2020] [Robert 1996] [Da Cás 2021] [Daniel et al. 2016] [Daniels and Saavedra 1994] [Darrow and Smith 1965] [Davis 2010b] [Davis et al. 2015] [Davis 2010a] [Deese et al. 1991] [Degtyarev et al. 2006] [Delamata et al. 2010] [Della Posta et al. 2026] [Delurgio et al. 1997] [Military Standard 1994] [Dergarabedian and Ten Dyke 1959] [Der Kiureghian 2001] [Desloire 2000] [Development Tendency of Space 2015] [Dickinson 1975] [Dickinson et al. 1964] [Dippolito and Stambolian 2011] [Dissel et al. 2005b] [Donahue 2016] [Donahue and Ziglar 2025] [Donlan and Brazill 1976] [Doreswamy and Self 2007] [Dorsey et al. 2000] [Dorsey et al. 1999] [Dotson 2001] [Dotson and Engblom 2002] [Dotson and Engblom 2004] [Dragone 2000] [Draim and Stalzer 1960] [Dumbacher 2002] [Dumbacher 2006] [Dumbacher and Klevatt 1994] [Dumbacher and Reuter 2007] [Duprey and Saucier 2008] [Ebrahimi et al. 2011b] [Gorfad Vijaykumar Devraj 2016] [Elkman et al. 2011b] [Elkman et al. 2011a] [Elvin 1996] [Ensworth 2003] [Ericsson and Guenther 1971a] [Erol and Ünsal 2026] [Estimating the Mass 2015] [Eymar 2003] [Eymar and Obersteiner 2004] [Factor and Stipandic 1982] [Fallon et al. 1999] [Ferrone and Nguyen 2010] [First Rocket Launch 2008] [Firsyuk et al. 2025] [Fishel 1981] [Fishel 1982] [Fowler 1963] [Fox and Glass] [Fragola 2012] [Freeborn et al. 2005] [Freeman et al. 1996] [Freeman et al. 1997] [French 2010] [Froning 2006] [Fujii et al. 2003] [Gabris et al. 1984] [Gage and Vander Kam 2003] [Galbreath and Franke 2001] [Gallucci et al. 2012] [Gardinier and Taylor 1999] [Garvey and Besnard 2005] [Garvey and Besnard 2006] [Gea et al. 2000] [General Dynamics Corp San Diego Ca 1992] [George 1966] [Gillespie 2004] [Dhanush et al. 2019] [Glass and Belvin 2003] [Go Horizontal 2004] [Godai 1987] [Goldyn et al. 2025] [Gomersall and Brunk 1968] [Gong 2017] [Goodrum and Smolensky 1965] [Goodstein et al. 1984] [Gord et al. 1994] [Rifà 2022] [Greaves 1997] [Greenberg 1996] [Greene 1994] [Greene et al. 1990] [Griffin and Pendleton 2008] [Grishko et al. 2025] [Guarro and Tomei 2004] [Guikema and Paté-Cornell 2005] [Gülgönül and Sözbir 2018] [Gunn 1973] [Guo et al. 2011] [Gusman et al. 2011a] [Haberbusch et al. 2002] [Hagopian 2002] [Hall 1992] [Hall et al. 2011a] [Hannigan et al. 1993] [Hanson and Beard 2010] [Hanson et al. 2011] [Hanson and Pinson 2011] [Hanson and Pinson 2012] [Hao et al. 2022] [Hardy et al. 1993] [Harris 1968a] [Heaney et al. 2021] [Herron et al. 2016] [Hidalgo 2000] [Higgins 2007] [Hinckel 1995] [Historical Perspective on Space 2001] [History of Rockets & 2022] [Holland and Shaw] [Honeycutt et al. 2020] [Honeycutt et al. 2016] [Hosseini et al. 2011] [Hou and Gramoll 1998] [Houston et al. 2015] [Hrinda 2009] [Huang and Brown 1967] [Huangpeng et al. 2022] [Hudson 1998] [Huebner et al. 2009] [Hueter 1995] [Hung and Hunt 1964] [Hunley 2008b] [Hunley 2008h] [Hunley 2008i] [Hunley 2008f] [Hunley 2008g] [Hunley 2008e] [Hutt 2003] [Imoto 2016] [Inatani et al. 1999] [Intelligent Fault Diagnosis 2015] [ISAS’s New Launch Vehicle 1990] [Ishida et al. 2006] [Ishimoto et al. 2005] [Islam 2024] [Jacobs et al. 2005] [Jain et al. 2011] [Jain and Trost 2013] [Jakhu and Pelton 2017] [Jalaja et al. 2023] [Jategaonkar et al. 2006] [Jensen 2000] [Jha et al. 2006] [Jha et al. 2010] [Jha et al. 2011] [Jia et al. 2020] [Johnson 1990] [Johnson and de Almeida 2008] [Johnson et al. 2006a] [Johnson and Servidio 2008] [Boustani et al] [Jung et al. 2023a] [Junker 1973] [Kaplan 2002] [Karel 1967] [Kelley 2012] [Kelly et al. 2009] [Kibbey 2015] [Kim et al. 2026a] [Kim et al. 2021] [King et al. 2009] [Kinnersley et al. 2003] [Kitsios and Lygeros] [Klemen 2015] [Klevatt 1995] [Klyushnikov et al. 2014] [Kniss 1968] [Ko et al. 2006] [Koelle 1990] [Kohrs 1982] [Kohrs and Petersen 1998] [Komatsu et al. 2000] [Kondratiev 2019] [Krause 1990] [Krivenko 2026] [Kross and Webb 1979] [Kudryavtsev and Safronov 2012] [Kurela et al. 2024] [Kurela et al. 2025] [Kuzin et al. 2009] [Landis et al. 2000] [Launch vehicle dynamics] [Launch Vehicle Performance 1963] [Launch Vehicle Booster Avionics 2000] [Launch Vehicle Systems 2022] [Launch Vehicle Manufacturing 2022] [Launch Vehicle Stress Analysis 2022] [Launch Vehicle Performance 2022] [Launch Vehicle Financial Analysis 2022] [Launch Vehicle Systems] [Laursen 1994] [Laursen and Voce 1996] [Lebeau and Orye 1976] [Leendertse 1961] [Leingang et al. 1993] [LeMoyne 2005] [Lentsch et al. 2003] [Letchworth and Letchworth 2000] [Levine 1964] [Li et al. 2026a] [Li et al. 2022c] [Li et al. 2024a] [Liao et al. 2023a] [Liever and Habchi 2004] [Liu et al. 2025i] [Livingston 2008] [Logsdon and Williamson 1997] [Long March Launch Vehicles 1990] [Losik 2010a] [Losik, Ph.D. 2012b] [Losik, Ph.D. 2012a] [Lou et al. 2025] [Loughrey] [Lyles 1999] [Lynch 1970] [MacLean and Rodriguez 1996] [Maekawa 1996] [Magistro et al. 2025] [Mammen et al. 1993] [Mani et al. 2004b] [Manning et al. 2010] [Manokaran et al. 2009] [Manwatkar et al. 2017] [Manwatkar et al. 2024] [Manwatkar et al. 2016] [Martin 2006] [Martin et al. 2024a] [Martin Co Baltimore Md 1963] [Martindale 2006] [Mathias et al. 2008] [May and Lyles 2014b] [May and Lyles 2014a] [Mazzone et al. 2024] [McCaskill 1970] [McClure 1998] [McCurdy and Roche 2004] [McCurry 1996] [McDavid et al. 2008] [McDermott et al. 1994] [McInerny 1996a] [McInerny 1996b] [Mehta et al. 2023] [Mehta and Steva 2024] [Messinger 2000] [Meyerson 1998] [Meyerson and Taylor 2001] [Michalski and Johnson 2007] [Mihara 1988] [Mileti et al. 2008] [Miller 1963] [Milliken 1963] [Miyazawa and Fukushima 1991] [Mohan and Kishore 2021] [Molina et al. 2009] [Monell et al. 2006] [Monk et al. 2012] [Morgenthaler and Montoya 1991] [Mori et al. 2016] [Morino et al. 1987] [Morris 1970] [Moser 1965] [Mrazek 1964] [Mueller 1964] [Murugesan et al. 2017] [Murugesan et al. 2018] [Naftel and Powell 1985] [Nair and Kukreja 2025] [Networks of Testing 2015] [Ngo et al. 2017] [Nilsen et al. 2005] [Nola and Blue 2008] [Noneman 2002] [Novykov et al. 2015] [Connor 1965] [Oconnor 1966] [Olalekan et al. 2026] [Overview of Testing 2015] [Pamadi et al. 2006] [Pamadi et al. 2016] [Panda 2019] [Park and Seo 2016] [Parkinson 1991] [Paschall and Brady 2014] [Patel 2013] [Pei et al. 2014] [Pelton and Madry 2019] [Pelton and Madry 2020] [Perspectives in Space Transportation 1988] [Phillips et al. 2007] [Pidvysotskyi 2021] [Pinier 2011] [Pinier 2012] [POGO Prevention of H-2 1994] [Powell 1962] [Prasad 2022] [Priskos 2016] [Proroka and Lypovskyi 2019] [Qi et al. 2024] [Qing et al. 2016] [Qu et al. 2004] [Raftery and Caluori 1990] [Rahman 2018] [Rahn et al. 1998] [Ralph 1965] [Rapp 2025a] [Rasky et al. 2006] [Rasky 1998] [Rathnavel et al. 2017] [Raymond and Kendall 2019] [Reaser 1997] [Design Engineering Committee 1999] [Space Launch Integration Committee 2001] [Reed et al. 2016] [Reichert and Buzzard 1995] [Reusable Launch Vehicle 1995] [Reusable Launch Vehicle Landing 2026] [Review of Dynamical Analysis 2026] [Rey 2000] [Riebe et al. 1981] [Rivers 1999] [Robertson] [Robinson et al. 2004] [Rogers 1965] [Rogers and Dragone 1996] [Rohrschneider and Olds 2001] [Romano et al. 2024b] [Romick et al. 1958] [Rooney 2003] [Rothschild et al. 2005] [Runkle and Wolf 1995] [Ruppe 1987] [Rusch and Sharples 2000] [Ryan and Verderaime 1993] [Sabaghzadeh and Khansari 2022] [Sanford et al. 2003] [Satellite Installation and Launch] [Sawyer and Bush 1998] [Schieb 2006] [Schiffer 1964] [Schmidt and Mann 1996] [Schoneman et al. 2003] [Seiler et al. 2008] [Sekula et al. 2012] [Shaw et al. 2005] [Shin and Park 2026] [Singer 2012] [Singer et al. 2013] [Singer et al. 2008] [Singh et al. 2024c] [Sippel et al. 2001] [Sippel et al. 1999] [Sippel et al. 2003] [Sivan and Pandian 2018] [Smith 2011] [Snoddy et al. 2006] [Somanath et al. 1999] [Sowers 2002] [Space Launch Vehicles Configured 1998] [Space Launch Vehicle Structures 2022] [Space Shuttle Solid Rocket 1973] [Space systems � Launch-vehicle-to-spacecraft] [Space systems. Spacecraft-to-launch-vehicle interface] [Space systems. Spacecraft interface] [Space systems. Requirements of] [Space systems. Space launch] [Space systems. General test] [Space Transportation 1988] [Spencer 1999] [Springer 1994] [Stadler 1998] [Staniszewski 1999] [Staniszewski 2001] [Stanley and Powell 1990] [Stanley et al. 1993] [Steffens and Mavris 2015] [Steinmeyer and Frick 2015] [Stockinger et al. 2005] [Strobl et al. 2012] [Surender et al. 2021] [Suresh] [Surzhikov 1999] [Szatkowski 1991] [Szedula 1996] [Taliaferro and Darr 2024] [Tanaka 1990] [Tatry et al. 1997] [Tatsukawa et al. 2011] [Tayefi et al. 2012] [Taylor et al. 1997] [Tetik and Das 2017] [Tetlow et al. 2000] [The Construction 1931] [The Goddard Rocket 1931] [Tobbe et al. 2009] [Toker et al. 2003] [Torisaka and Yamakawa 2008] [Trevino et al. 2012] [Trout et al. 2009] [Trout et al. 2011] [Truax and Ryan 1961] [Tsutsumi et al. 2014] [Tuohy 1998] [U. S. Rocket Development 1949] [U.S. Access to Space 1990] [Ujino 2000] [Ujino et al. 1989] [Usmonov and Kretov 2020] [Vaglio-Laurin and Finke 1965] [Vaheed et al. 2024] [Villanueva 2018a] [Villanueva 2022] [Villanueva et al. 2013a] [Villanueva et al. 2014] [Wagner 1999] [Wagner and Yingling 1998] [Wailes and Carlson 1986] [Wallace et al. 2003] [Wang and Miao 2026] [Wang et al. 2024b] [Wangu and Mouyos 1998] [Ward 2015] [Wente 1982] [Whitehead 1990] [Whitehead 2005] [Williams et al. 2018] [Winnick 1996] [Wolfe 1966] [Woo et al. 1994] [Wu et al. 2013] [Wu and Zhang 2023] [Yang et al. 2006] [Yang et al. 1999] [Yaranton] [Yeniay et al. 2006] [Yenigelen and Morris 2020] [Young 1997] [Young 2015] [Young 2025b] [Young 2025c] [Young 2025a] [Yunis 2005] [Yunis 2007] [Zhang et al. 2018a] [Zhou and Mi 2024] [Zhou et al. 2015]
The corridor, and the trajectory that has to stay inside it
The keystone stated as a literature. Dynamic pressure as a constraint, ascent guidance under it, and the loss accounting that decides how much propellant a condition costs.
710 records. [§ 5. the Free 2014] [Abdulkerim 2022] [Adelfang 2003] [Adelfang et al. 1994] [Adelfang and Smith 1998] [Adimurthy 1976] [Adimurthy 1987] [Aditya Chowdhury , Vishnu G Nair and TJPRC 2017] [Adkins 1965] [Akbulut et al. 2011] [Al Bakri] [Albarado et al. 2010] [Al-Garni and Kassem 2005] [Amberkar et al. 2020] [An et al. 2020b] [An et al. 2026] [Anderson 1970] [Anderson and Watt 1971] [Approximate Analysis 1986] [Ardema et al. 1994] [Arora and Ananthasayanam 2003] [Arora et al. 2003] [Ascent guidance for an 1994] [Ascent Trajectory Analysis 2022] [Aso 2017] [Barbosa et al. 2016] [Barr et al. 2026] [Bartusiak et al. 2023] [Bataleblu and Roshanian 2015] [Battle and Gottlieb 1964] [Beltracchi and Nguyen 1992] [Benedikter et al. 2025] [Benedikter et al. 2021] [Benedikter et al. 2022] [Benito and Johnson 2016] [Benito and Shotwell 2017] [Berend and Talbot 2006] [Bhavnani and Robinson 1979] [Boehm et al. 1969] [Bonavita et al. 2026] [Boost Trajectory Estimation 2024] [Bordachev and Kolga 2024] 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The engine, which is the only part of the vehicle that is not a structure
The largest cluster, and that is a fact about rocketry rather than about this vehicle. Liquid propulsion dominates it, and throttling, gimballing and combustion stability are all in here because the X-60A’s ground campaign demonstrated all three.
1,811 records. [Alexander et al. 2011] [Park 2005] [Abada et al. 2024] [Acoustic Sensitivity Measurements 1996] [Adler et al. 1991] [Advisory Group for Aerospace Research and Development 1979] [Aerojet-General Corp Sacramento Ca 1963] [Aerojet-General Corp Sacramento Ca 1966] [Afzali et al. 2009] [Ageenko et al. 2013] [Ahrazoğlu 2023] [Akbulatov et al. 2026] [Akbulatov et al. 2023] [Alcock and Hagar 1989] [Alden and Habert 1964] [Alexandrov 2026] [Alhama and Campo 2003] [Ali and Crawford 1988] [Ali and Gupta 1990] [Ali and Borrer 2013b] [Ali and Borrer 2013a] [Altman and Lorell 1952] [Alves Almeida et al. 2024] [Amano and Yen 2015] [Amateur Gas-Propelled Rocket Engine 2004] [Swanger and Nacif 2022] [An Equivalent Propellant Sloshing 2018] [Anafi and Qasem 2025] [Analysis of Pressure Feasibility 1960] [Analysis of a New 1960] [Ananoff 1941] [Anderson et al. 2009] [Anderson et al. 2015] [Anderson et al. 2012] [Andrews et al. 1965] [Andrews et al. 1966] [Anikina et al. 2026] [Kala et al. 2027] [Anoop et 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Solid and hybrid rocket motors
Solid and hybrid motors as propulsion units, being their performance, ignition transients, internal ballistics, grain mechanics, testing and history, because the sounding rockets this vehicle is compared with are solid motors that burn briefly and hard.
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What rides in the nose, which is why the corridor has to be held
The payload the corridor exists for. Supersonic combustion, inlets, isolators and the dual-mode transition, with the ramjet, ducted-rocket and combined-cycle engines around them, which is the reason a dynamic pressure band is a specification rather than a preference.
1,036 records. 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Surviving the heat, which is a materials problem before it is a flow problem
Thermal protection, placed above aerothermodynamics on purpose. A hot structure is a special case of a heated flow field, and the general cluster placed first would take the materials literature into it.
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Aerothermodynamics, which is what the corridor does to whatever is in it
Stagnation conditions, transition and real-gas behaviour. The relations this article evaluates for the corridor table are all from here.
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Making hypersonic conditions on the ground, and why that is not enough
The facilities the programme was arguing against. Shock tunnels, arc heaters and expansion tubes, each of which reaches part of the condition, and the capability-gap assessments that say which part.
651 records. 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1995] [Orth and Kislykh 1996] [Ozawa et al. 2014] [Palma et al. 1998b] [Palma et al. 1993] [Palma et al. 1998a] [Palmer and Hanson 1995] [Palmer et al. 1992] [Panfilov et al. 2021] [Park et al. 2004] [Park et al. 2006] [Parker et al. 1992b] [Parziale et al. 2012] [Parziale et al. 2014] [Paull 1996a] [Paull 1996b] [Paull et al. 1988] [Penland and Romeo 1971b] [Penland and Romeo 1971a] [Plumadore et al. 2025] [Plumadore et al. 2026] [Pope and Maydew 1959] [Prabhu et al. 2009b] [Prabhu et al. 2009a] [Principles of Hypersonic Test 2002] [Purpura 2021] [Raezer et al. 1963] [Raj et al. 2019] [Rasmussen 1968] [Rault 1992b] [Reddeppa et al. 2009] [Reddy 1978] [Reddy et al. 2017] [Reed and Hiers 2021] [Resch et al. 1992] [Reubush et al. 1987] [Rhode and DeLoach 2005] [Richards 1979] [Richards and Enkenhus 1970] [Rom et al. 1995] [Rossmann 2003] [Syam et al. 2026] [Saenz et al. 2025] [Sanchez-Gonzalez et al. 2012] [Sanderson and Simmons 1991] [Saravanan et al. 2008] [Saravanan et al. 2009] [Sasoh et al. 2001] [Sauerwein et al. 2015] [Scaggs 1966] [Scaggs et al. 1963] [Schemperg and Mundt 2008] [Schemperg and Mundt 2009] [Schindel 2005] [Schneider 2000] [Schneider 2007a] [Schneider 2009] [Schulz and Bauer 1972] [Schwartz et al. 2025a] [Schwing 2000] [Scott] [Segal 2011] [Segura 2007] [Seiff 1954] [Seiler et al. 2012] [Selcan et al. 2019] [Selcan et al. 2021] [Sellers and Dwoyer 1993] [Serre 2009] [Serre et al. 2011] [Serre and Falempin 2008] [Sevcenco et al. 2015] [Shams et al. 2018] [Shang] [Sharma and Wilson 1995] [Shea et al. 2023] [Sheeley et al. 2006] [Shekhtman et al. 2021b] [Shen et al. 2019] [Shreeve et al. 1961] [Simmons 2000] [Simmons et al. 1989] [Sivells 1963] [Sivells 1969] [Skinner and Stalker 1996] [Skinner and Stalker 1995] [Smelt and Turner 1958] [Smith and Carver 1993] [Smith et al. 1969] [Smith et al. 1987b] [Smith and Lewis 2004] [Smith and Dutta 2017] [Space systems - Ground] [Spearman 1979] [Sriram et al. 2015] [Sriram and Jagadeesh 2016] [Stacey and Simmons 1992] [Stainback and Wagner 1972] [Stalker 1965] [Stalker 1966] [Stalker 1967] [Stallings et al. 2003] [Starshak and Laurence 2021] [Stennett] [Stennett et al. 2018] [Stennett et al. 2019] [Stennett et al. 2020] [Sterling et al. 1998] [Stewart 1993] [Stokes 1961] [Stollery 1995] [Strike et al. 1974] [Stuessy et al. 1996] [Stuessy et al. 1990] [Sudani et al. 1997] [Sudhiesh Kumar and Reddy 2015] [Surzhikov 2021b] [Surzhikov 2021a] [Suzuki et al. 2012a] [Sylvester 1967] [Taguchi et al. 2014] [Gokcen] [Gokcen] [Tai et al. 2001] [Takahashi 2027] [Takahashi et al. 2009] [Takahashi et al. 2023] [Tang et al. 2019] [Tani et al. 1994] [Tanno et al. 2009a] [Tanno et al. 2013b] [Tanno et al. 2013a] [Tanno et al. 2015] [Tanno et al. 2018] [Tanno et al. 2019a] [Tate 1964] [Teixeira and Páscoa 2024] [Tepe et al. 1963] [Terrazas-Salinas and Craig 1989] [The Duration and Properties 1962] [The SCIROCCO 70-MW Plasma 2002] [Thirani et al. 2024a] [Thirani et al. 2024b] [Thirani et al. 2025] [Thomas and Perlbachs 1967] [Thomas et al. 1995] [Thompson et al. 2011] [Thornton et al. 2021] [Tirres et al. 2002] [Tirtey et al. 2006] [Trimmer et al. 1986] [Tsirkunov and Verevkin 2013] [Tumuklu et al. 2021] [Tuohy 2006] [Turner 1965] [Tuttle] [Tuttle et al. 1994] [Ueno et al. 2002] [Use of Arc-Jet Hypersonic 1980] [Uselton 1976] [van den Herik et al. 2025] [Varwig 1963] [Vaughn and Garrard 2011] [Venkatapathy et al. 2018] [Veraar 2009] [Vicente and Foy 1963a] [Vicente and Foy 1963b] [Vo] [Voland et al. 1998] [Wagner and Dale 1985] [Wagner et al. 1990] [Walchner et al. 1969] [Walpot et al. 1996] [Wang et al. 2015] [Wang and Jiang 2020] [Wang et al. 2017e] [Wang and Lin 2016] [Wang et al. 2016a] [Wang et al. 2016b] [Wang et al. 2017c] [Wang et al. 2019a] [Wasilczuk et al. 2024] [Watt and Aronson 1964] [Weatherston 1969] [Weeks 1969] [Weeks 1970] [Wegener and Lobb 1952] [Weiler et al. 1972] [Wells 1987] [Wen et al. 2009] [Wey et al. 2012] [Weyers] [Whitside et al. 2019] [Wilcox et al. 2016a] [Wilcox et al. 2016b] [Wilder and Reda 2004] [Willett et al. 1993] [Wilson 1990] [Wilson and Arnold 1994] [Wind-Tunnel Study of Ascent 1981] [Wing] [Winkler 1952] [Wittliff 1983] [Wittliff et al. 1992] [Wittliff and Wilson 1961a] [Woike and Willis 2000] [Woike and Willis 2001] [Wonnacott and DeMauro 2025] [Woods and Thompson 1993] [Woods et al. 2000b] [Yan et al. 2019] [Yang et al. 2024c] [Yi et al. 2019] [Yoshinaga et al. 1995] [Yu 2005] [Yu 2015] [Yu et al. 2022a] [Yu et al. 1992] [Yu et al. 2022b] [Yu et al. 2024b] [Yu et al. 2025a] [Yu et al. 1994] [Zafar et al. 2022] [Zhao et al. 2005] [Zhu and Jiang 2021] [Zhu and Laurence 2023]
Measuring a flight that lasts a minute
Instrumentation, telemetry and the reconstruction of a trajectory from what survived. A test that lasts seconds has to be instrumented before it flies.
267 records. [Ahearn et al. 1957] [Aircraft and Flight Test 2021] [Air Force Flight Test Center Edwards AFB CA 1974] [Air Force Test Pilot School Edwards Afb Ca 1990] [Air Force Test Pilot School Edwards Afb Ca 1993] [Alich and Castillo 2007] [Anderson et al. 2021b] [Berecz 1974] [Berg 1968] [Berman et al. 2025] [Bettis et al. 2011] [Beyers et al. 1962] [Blackstock and Theobalds 2005] [Bland et al. 2006] [Bleimeyer 1981] [Blem and Gülhan 2026] [Blodgett et al. 1986] [Blue and Crawford] [Blue and Crawford 1997] [Bohley and Caldecott] [Böhrk 2015] [Bolt 1981] [Bowser and Busch 1966] [Boyer 1965] [Brailsford 1992] [Brandon et al. 2001] [Brevault] [Brooks 1986] [Brune et al. 2015] [Brune et al. 2019b] [Bryan 1953] [Bull 1999] [Bull et al. 2001] [Butler et al. 2022] [Buzzo 1992] [Cassanto 1966] [Cato 1964a] [Cato 1964b] [Cato 1965a] [Cato 1965b] [Cattolica et al. 1992] [Cattolica et al. 1990] [Cavolowsky and Newfield 1992] [Chai and Wilhite 2010] [Chan and Singh] [Chavez and Schmidt 1994] [Chen 2021] [Chen et al. 2018c] [Chen et al. 2018b] [Cipollini and Muylaert 2006] [Clingenpeel et al. 2026] [Cockrell and Doherr 1981] [Cooke 1980] [Costello et al. 2021] [Crawford and Thomas 2006] [Crosswy and Kalb 1967] [Cullon and Lezberg 1972] [D’Amico et al. 2004] [Danowsky et al. 2012] [D’Antuono et al. 2024] [Crounse 2005] [Delmonte 1967] [Design Validation and Verification 2026] [Deyst 1968] [Dickhudt 1983] [Dorobantu et al. 2013] [Duke and Lux 1983] [Dupuis and Edwards 1998] [Durbin 1959] [Robert et al. 2017] [Eastman 1992] [Ebacher 1979] [Schwegler - Lanl and Place - Honeywell 2000] [Eliassen 1965] [El-Kebir and Ornik 2020] [End-To-End Flight Test Data 2020] [Esposito et al. 2022] [Fain et al. 1970] [Fan et al. 2016] [Fateih 1992] [Feie and Kretz 2008] [Feng et al. 2019] [Fisher 1971] [Flight Test Instrumentation 1965] [Förder and Steiner 2020] [Frankenthal 1964] [French et al. 1970] [Gardner 1966] [Garg and Dodiyal 2009] [Gilcrease 1982] [Godwin et al. 1964] [Grabowsky et al. 1981] [Grace 2001] [Grauer and Boucher 2017] [Gray 2014] [Gray 2015] [Griffiths et al. 2016] [Guo and Liu 2024] [Hadady 1959] [Hager 1955] [Hansman and Kang 1988] [Hao and Wang 2023] [Hellbaum and Garner 1988] [Hensley 1994] [Herget 1965] [Herzog et al. 1998] [Higgins 1959] [Highsmith et al. 2015] [Howland 1953] [Hu et al. 2018] [Hudson] [Hulshoff et al. 1996] [Hurst and Collins 2008] [In-Flight Thrust Determination] [Ince 1967] [Ito et al. 1999] [Janardhanan 1982] [Jann and Yakimenko 2015] [Jenkins 1962] [Jia-Ming et al. 2024] [Jiang et al. 2018] [Johnson et al. 2009b] [Johnson and Crawford 2011] [Jones 1993] [Kain et al. 1978] [Kaletka and Fu 1993] [Kanner and Hengel 2001] [Kays and Olsen 1967] [Kim et al. 2019] [Kish et al. 2017] [Klingenberg et al. 2026] [Klyde et al. 2004] [Kokolios 1994] [Korsun et al. 2024] [Kotel’nikov et al. 2020] [Kulakhmetov et al. 2024] [Lalithambika and Dasgupta 2007] [Lamy 1983] [Lane et al. 2000] [Lane et al. 2001a] [Large et al. 1981] [Li et al. 2022b] [Lightweight Low-Cost Flight Test 2007] [Liu et al. 2022a] [Liu et al. 2025h] [Losik 2010c] [Luecke 1957] [Lutfy and Muntz 1995] [Lutfy and Muntz 1996] [Machnik et al. 2022] [Mackey et al. 2018] [Madhavan 2000] [Mannai 1962] [Massa and Schetz 2020] [Mayer and Chalfant 2023] [McAlister and Thompson 1970] [McDowell and Williamson 1980] [Meckler 1965] [Mengers et al. 2007] [Methods for Reducing Data 2003] [Miles et al. 1983] [Montgomery and Conard 1980] [Moore 1986] [Morelli and Klein 1995] [Ryu 2009b] [Musal et al. 1964] [Neely and Tjong 2008] [Neely and Tracy 2006] [Nelius and Harris 1965] [Nelson 1969] [Netzel et al. 2025] [Boutier 1993] [Newell and Zakharov 2007] [Nicoll 1962] [Oelker and Friehmelt 1998] [Okojie et al. 2009] [Orr et al. 2014] [Owen and Owen 2007] [Venkataramana et al. 2023] [Pace et al. 2015] [Palomino 2022] [Parks and Bach 1990] [Pawlak 1994] [Pelt et al. 2026] [Petersen 1981] [Piazza et al. 2009] [Platz and Bounajem 1992] [Plender 1964] [Plumadore et al. 2023] [Poderico et al. 2012] [Prades et al. 2016] [Ravindra et al. 2023] [Rehman et al. 2009b] [Renz et al. 1981] [Rhoads et al. 2026] [Ricciardi and Minwalla 2016] [Dillman et al] [Dillman et al] [Rochefort et al. 1974] [Rodrigues et al. 2005] [Rooker 1970] [Rose et al. 2009] [Roseberry 2025] [Rosenberg and Schuch 1983] [Ross and Elbert] [Rudolph 1986] [Sandoz et al. 2024] [Sandoz and Klaeyle 2021] [Sarkar et al. 2009] [Sarkar and Panneerselvam 1998] [Schrader 2023] [Schumacher 1952] [Shi et al. 2011a] [Shou and Li 2026] [Simpson 1972] [Simpson 1979] [Skarman 1978] [Son 2018] [Song and Choi 2018] [Space systems. Launch-vehicle-to-spacecraft flight] [Spravka and Jorris 2015b] [Spravka and Jorris 2015a] [Starkey 2003] [Sternberg 2010] [Stilley 1988] [Swanson and Cassell 2011] [Swenson et al. 2026] [Takahashi et al. 2025a] [Takahashi et al. 2026] [Takaki et al. 1997] [Tarshis and Sakoda 1979] [Taylor 1986] [Taylor 2012] [Time-Dependent In-Flight Thrust Determination] [Ueno et al. 2004] [Uncertainty of In-Flight Thrust] [Urban 1959] [Urban 1963] [Vemuri 1982] [Vijayan and Suresh Babu 2015] [Walter] [Wan et al. 2012] [Wang et al. 2002] [Weaver 1972] [Webb et al. 1962] [Wei-Min et al. 2012] [Weinell et al. 2026] [Wignall and Houlden 2020] [Benson et al] [Wilson] [Wingrove 1972] [Wolf and Bossert 2001] [Wortman 1969] [Wu and Yu 2018] [Xin 2023] [Yamada et al. 2022] [Yanagihara et al. 1997] [Yang 2021b] [Yang 2021c] [Yang 2021a] [Yao and Hao 2023] [Yu et al. 2020] [Zhang et al. 2010a] [Zhang et al. 2024c] [Zhang et al. 2014d] [Zhang et al. 2023h] [Zhao 2021c]
Flight research programmes and the practice of flight test
How research flight is planned and run, for the lifting bodies, the X-29 and the high-speed and entry vehicles whose flight test programmes are the comparison for a programme that never flew.
39 records. [Abe et al. 2001] [Adams and Graves 1983] [Armstrong 1977] [Czysz et al. 1997] [Bushnell 1997] [Draper et al. 1977] [Driscoll and Eckenroth 1976] [Dupuis and Edwards 1995] [Free Flight Research Tool 1956] [Gentry et al. 1966] [Grantz et al. 1993] [Groener et al. 1980] [Iliff and Shafer 1993] [Iliff and Shafer 1995] [Jorris 2014] [Kidd 1965] [Manke and Love 1975] [McClinton et al. 2002] [McQuellin et al. 2020] [McTigue and Ryan 1968] [Minami and Tsukamoto 2006] [Mori et al. 2002] [Murphy and Rubesin 1966] [Parks and Waldman 1990] [Putnam 1983] [Richards and Monaghan 1997] [Rigali et al. 1980] [Roudakov et al. 2001] [Sacher 1993] [Sakurai et al. 1997] [Sefic and Maxwell 1986] [Semenov et al. 2001] [Stewart and Bauer 1983] [Stone and Koch 1979] [Thompson 1966] [Thompson 1970] [Trippensee and Lux 1987] [Walters and Butler 1992] [Williamson 1992]
Range safety, licensing and the rules a rocket flies under
The regulatory literature, which is where the question of what this vehicle legally was would have been answered had it flown.
379 records. [Tharun et al. 2025] [Abernathy et al. 1999] [Adams and Petrov 2006] [Aerospace Corp El Segundo Ca 1963] [Rao et al. 2025] [Aktas et al. 2016] [Albat 2014] [Alkhaleefah and Marais 2024] [Allison 2017] [Alves, F and Keith 1995] [Anderson et al. 2021a] [Appendix K 2008] [Archer 2000] [Arisandi 2017] [Arriola 2018] [Asamura et al. 2024] [Autry 2021] [Baccini 1996] [Bachner and Hynes 2018] [Backus 1971] [Bailey and Linder 1983] [Barbre et al. 2019] [Barker et al. 2024] [Barker and Marais 2026] [Bartone et al. 2001] [Battie et al. 2012] [Beaty et al. 2008] [Beaty 2011] [Bentley 2009] [Benton 1987] [Best et al. 2004] [Beyma 1986] [Bibhorr and Anand 2021] [Birkeland 2000] [Birkeland and Meuser 1999] [Birkmire and Gallagher 2012] [Bojorquez and Chen 2019] [Bowles and Lang 1993] [Boy et al. 2018] [Williams et al] [Braun et al. 1970] [Breda et al. 2025] [Breda et al. 2026] [Brennan et al. 2009] [Brennan et al. 2010] [Brinton et al. 1994a] [Brughelli 2002] [Button 2013] [Buzzatto] [Çam and Özkol 2023] [Capristan and Alonso 2014] [Cass and Schooff 1999] [Catena et al. 2001] [Chen et al] [Chuang and Ledsinger 1996] [Clapp 1995] [Claxton and Linton 2002] [Coleman 2024] [Coleman et al. 2024] [Commercial Human Space-Flight Vehicle 2010] [Corl et al. 2014] [Davidian 2017] [Davidian 2019] [Davidian 2020] [Debris from Spallation 1984] [de Dalmau 1996] [Del Casal 1983] [Delgado 2012] [Demidovich 2017] [Environmental Impact Analysis Process. 1988] [Environmental Impact Analysis Process. 1989b] [Environmental Impact Analysis Process. 1989a] [Diana et al. 2018] [Dolvin 2009] [Dong et al. 2019a] [Dronzek 1991] [Duce and Nenni 1995] [Ecological Aspects of Rocket 2013] [Ecological Aspects of Rocket 2016] [Ellzey 2021] [Endicott 1999] [Endicott and Franke 1999] [Erdos 1977] [Falco et al. 2023] [Ferrell 2001] [Fevig et al. 2022] [Finger et al. 2007] [Finger and McClesky 2010] [Fleeter 2000] [Francine and Stewart 1995] [Freitas and Chocron 2008] [Frick and Foster 2010] [Fuller and Minami 1992] [Gallien 1990] [Garegnani et al. 2024] [Gaver and Jacobs 1997] [Gee and Mathias 2008] [Gente et al. 2024] [Gorelyi et al. 2008] [Goswami 2013] [Gourab et al. 2021b] [Gourab et al. 2023b] [Gourab et al. 2021a] [Gourab et al. 2023a] [Gray and Colloredo 2012] [Greenberg 1993] [Greenberg 2000] [Guikema and Pate-Cornell 2003] [Gujral and Emdee 2016] [Gulliver and Finger 2010] [Gulliver et al. 2017] [Guo et al. 2025a] [Güven and Goel 2024] [Haber et al. 2013b] [Haber et al. 2013a] [Hall et al. 2011b] [Hancock 2005] [Hanlon 2019] [Harvey 1980] [Hays et al. 2024] [Hayward 1992] [Heald and Jones 1973] [Heatwole and Lanzi 2010] [Herbella et al. 2011] [Hertzfeld 2000] [Heydon 1996] [Hoffman and Pelton 2010] [Holubek 2020] [Hosangadi and Madavan 2008] [Howell 2025] [Howison 1967] [Hughes and Rosenberg 2005] [Huynh and Kriz 2009] [Hwang et al. 2016] [Inokuchi 1996] [Ireland and Gonzales 2020] [Jackson and Smith 2000] [Ji and Zhou 2017] [Ji and Zhou 2018] [Ji et al. 2018] [Jianshuang Song et al. 2012] [Jo and Ahn 2020] [Kress et al. 2024] [Johnson 1965] [Johnson 2013] [Jones et al. 2021] [Justice 1965] [Kaltenhäuser 2024] [Kaltenhäuser et al. 2017] [Kanjumba 2025] [Kapelyushin et al. 2023] [Keene and Ahmed 2026] [Ken Gee and Lawrence 2013] [Kerolle 2017] [Kfir and Perry 2017] [Kim 2018] [Kim et al. 2008] [Knothe 1970] [Kobyzev et al. 2012] [Kopecek 1970] [Kuhns 2011] [Kumar et al. 2025] [Kumar et al. 2026a] [Kutty and Pratt 2010] [LaFarge 1994] [Lang et al. 2001] [Lang et al. 2002] [Lang et al. 2003] [Lanzi 2014] [Lanzi and Simpson 2010] [Larios-Barbosa et al. 2016] [Larsen 2000] [Larsen 2003] [Larsen 2005] [Larsen 2006] [Larsen 2007] [Las Cruces Spaceport 2015] [Lash et al. 2020] [Lauer 2006] [Launch Sites 2016] [Lawrence and Mathias 2008] [Lechniak et al. 2015] [Ledford 1967] [Lee 2008c] [Lee 2025] [Legal Problems of Developing 1990] [Letchworth 2011a] [Letchworth 2011b] [Leung et al. 2013] [Li 2025] [Liu et al. 2009b] [Liu et al. 2022d] [Lively 2025] [Losik 2010b] [Lowe] [Ma et al. 2024c] [MacWilliams et al. 2014] [Maginnis et al. 2025] [Marmaro 1999] [Mashchenko and Fedyakin 2009] [Matula and McCune 1998] [Maximizing Commercial Space Transportation 2007] [Mayhue 1962] [Mayrhofer and Sachs 1999] [Mayrhofer and Sachs 2001] [McCarthy and Lange 2010] [McCurley and Wentzel 1966] [McDonald et al. 2025] [Measuring the Impact 1980] [Merchant 2026] [Meredith 1985] [Meyers 1988] [Millard 2008] [Mineiro 2008] [Mineiro 2010] [Miquel Parra et al. 2024] [Missile Defense Agency Washington DC 2007] [Mitchell and Riley 2011] [Momose et al. 2023] [Montag et al. 1986] [Montgomery 1970] [Moon and Wells 1991] [Moore 1998] [Morehouse 2006] [Morrison and Robillard] [Mosley 1970] [Murray 2007] [Mutuel and Murray 2016] [Myers 1984] [Newman and Stahmann 1963] [Ngo and Doman 2002] [Nick and Buchaillot 2024] [Nicolini and Roviera 2014] [Nield et al. 2016] [Nield et al. 2013] [O’Neill and Hansman 2024] [Oren 2021] [Palmer et al. 1981] [Pandya 2008] [Parker 1967] [Parker 1968] [Parks et al. 2026] [Parrish 1992] [Parrish and Koby 2021] [Pasciuti et al. 2025] [Patera 2006] [Pedrosa et al. 2024] [Pelton 2010] [Pelton 2013] [Pelton 2016] [Petro 1972] [Petrone 1963] [Petrone 1965] [Petrone 1966] [Philipson 1995] [Phillips 2007] [Preyssl 1989] [Priyadarshini et al. 2023] [Purdy 1965] [Pustovharov 2026] [Puzanov et al. 2024] [Ragusa 1983] [Navidad et al. 2024] [Ramsden 1976] [Ko 2004] [Rapp 2025b] [Ratcliffe and Crane 2003] [Ratkevich et al. 2013] [Reed 2000] [Guodong et al. 2026] [Reyhanoglu et al. 2011] [Richardson 2024] [Richardson et al. 2014] [Rickman and Holquin 1962] [Risk to Space Shuttle 2006] [Hodson and Evans 2023] [Roberts et al. 2018] [Rongier 2013] [Ryberg and Guidi 2004] [Rymarcsuk and Haase 2000] [Safety Control of Space 2015] [Sahani et al. 2017] [Sapp 1966] [Sauvageau and Foster 1995] [Schäfer 2001] [Schrock and Humphries 2002] [Schuch and Fisch 2018] [Schuiling 1987] [Schuiling 1988] [Schuiling 1990] [Schuiling and Mayer 1989] [Schuiling and O’Connor 1998] [Scott 1990] [Sgobba and Kezirian 2016] [Shaffer 1988] [Sham 1995] [Shearer 1997] [Shukla and Woolsey 2018] [Sivathanu Pillai 2022] [Slivinsky et al] [Smith 2000a] [Smith 2000b] [Smith et al. 2023] [Solanyk 1993] [Sorge 2005] [Space systems. Spacecraft and] [Space systems. Re-entry risk] [Space systems. Re-entry risk] [Spaceport Design 2009] [Srivastava et al. 2015] [Stadd 2016] [Stallmer 2001] [Standard Classification for Descriptions] [Space Launch Systems Committee 1998] [Starr et al. 2011a] [Stone and Lindenmoyer 2006] [Stower 2024] [Stower 2025] [Straubel 1987] [Strauss and Ivanov 2016] [Streamlining Space Launch Range 2000] [Strom 2006] [Sundahl 2017] [Tao 2018a] [Tao 2018b] [Tao et al. 2016a] [Tarzwell and Colley 1979] [Taylor 2006b] [Thakur et al. 2019] [Thornton 1977] [Thorpe et al. 2015] [Thorpe et al. 2012] [Tierney 1993] [Tinoco et al. 2025] [Tinoco and McCarthy 2026] [Tinoco et al. 2020c] [Tinoco et al. 2020d] [Tinoco et al. 2020b] [Tkatchova 2011] [Tkatchova 2017] [Toleman 2011] [Toohey 2003] [Torres and Rohl 2006] [Tow 2009] [Tow 2010] [Tow and Arce 2007] [Tow and Arce 2008] [Tronchetti 2016] [Tuckman 1965] [Mirmina and Schenewerk 2022] [Van Scyoc 2000] [van Traa-Engelman 1993] [Varaprasad and Rao 2006] [Victor 1979] [Vigil and Marchi 1994] [Vilanova and Diógenes 2025] [Vogt 2026] [Wakimoto 2019] [Wang et al. 2026f] [Wassenbergh 1993] [Wassenbergh 1996] [Weber 1984] [Westat INC Rockville MD 2001] [Whiteman et al. 2005] [Wiener et al. 1969] [Wilde 2024] [Wilfong et al. 1996] [Williams and Corcoran 1963] [Wisecup and Pena 2009] [Wong 2001] [Wong and Cho 1985] [Xiao et al. 2019] [Yermoldina et al. 2026] [Zaker 1975] [Zapata and Murray 2008] [Zemoura and Farago 2025] [Zhang et al. 2023e] [Zhao 2015b] [Zhou et al. 2026b]
What a flight test costs, which is the programme’s stated reason for existing
The programme’s own argument, as a literature. Cost models, technology readiness and the economics of responsive access.
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Flying a slender finned body, and holding it together
Guidance, control, loads and aeroelasticity for a body that is nine calibres long and has almost no wing, and for the launch vehicles, missiles and finned rockets that share its shape.
597 records. 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Guiding and controlling a hypersonic or entry vehicle
Guidance, control and flight dynamics of hypersonic and entry vehicles, including the generic air-breathing hypersonic vehicle models, because holding a corridor is a control problem and autonomous control is one of the three technologies the X-60A was to mature.
230 records. [Abensur 1994] [Almeida 2021] [An et al. 2017] [Arrington et al. 1967] [August and Joshi 1996] [Austin] [Bao et al. 2023] [Beall et al. 2017] [Bhat and Lind 2009] [Bin and Hongxin 2006] [Bityurin et al. 1999] [Bolender and Doman 2005] [Bolender and Doman 2006] [Bolender et al. 2007] [Bowersox and Fan 2000] [Bu and Lei 2018] [Burkhardt and Schoettle 1996] [Buschek and Calise 1995] [Butt 2013] [Butt et al. 2010] [Calhoun 2000] [Caplin] [Chamitoff 1992] [Chao et al. 2022] [Chen 2017a] [Chen and Chen 1991] [Chen et al. 2017a] [Chen and Zhao 2019a] [Chen et al. 2019c] [Cheng et al. 2020] [Cheng et al. 2019a] [Chengbin Lian et al. 2012] [Coakley] [Costa and Sachs 2002] [Cox et al. 1995] [Crenshaw 1983] [Cui et al. 2026] [Cvrlje et al. 1999] [Dalle et al. 2011b] [Das et al. 2008] [Dickeson et al. 2010] [DiFranco 1971] [Ding et al. 2023a] [Ding et al. 2019] [Ding et al. 2023d] [Doman and Ngo 2002] [Dong et al. 2023b] [Dong et al. 2025] [Dutta and Bhattacharya 2010] [Efremov et al. 2023] [Falkiewicz et al. 2010] [Fan et al. 2024] [Fan et al. 2017] [Fan et al. 2015] [Feng et al. 2022] [Fiorentini et al. 2008] [Forbes-Spyratos et al. 2014] [Frendreis and Cesnik 2010] [Gockel 1993] [Gongjun 2014] [Goz and Theodoulis 2025] [Groves et al. 2005] [Guo et al. 2023a] [Guo et al. 2018] [Guodong Ning et al] [Gupta] [Hall et al. 1998] [Han et al. 2024] [Hartofilis 1965] [Herrlin and Gelderloos 1988] [Holm-Hansen et al. 2010] [Hou et al. 2023] [Hu et al. 2008] [Hu et al. 2015] [Hu and Meng 2017] [Huang 2021] [Huang et al. 2017] [Huang and Speyer 2022] [Huo et al. 2016] [Ishimoto et al. 1996] [Janardanan and Jayakumar 2006] [Ji 2011] [Ji et al. 2023] [Jiang et al. 2024] [Jianguo et al. 2016] [Jian-li and Yun-feng 2008] [Jie Wang et al. 2012] [Johannessen 1964] [Keshmiri 2008] [Keshmiri et al. 2006a] [Keshmiri et al. 2007] [Klock and Cesnik 2015] [Klock and Cesnik 2017] [Komatsu et al] [Kontis and Stollery 1996] [Kremer and Mease 1994] [Kryvoruka and Ashurst 1973] [Kulkarni et al. 2024] [Lee et al. 2007] [Li et al. 2017g] [Li et al. 2020b] [Li and Fu 2010] [Li et al. 2022a] [Li and Lv 2016] [Li et al. 2017a] [Lian et al. 2013a] [Lian et al. 2013b] [Liang et al. 2025] [Liang et al. 2021] [Liang et al. 2016b] [Lin et al. 1982a] [Liu et al. 2019f] [Liu et al. 2021b] [Liu et al. 2014c] [Liu and Liang 2025] [Liu et al. 2025g] [Lu and Jiang 2019] [Lubing et al. 2017] [Lubing et al. 2020] [Ma et al. 2017] [Maughmer et al. 1993] [McDowell and Williamson 1982] [Meng et al. 2019] [Meng et al. 2023a] [Miele and Venkataraman 1985] [Mo et al. 2022a] [Mooij 2023] [Myers et al. 1995] [Ngo and Blake 2003] [Ochi 2004] [Olsen 1965] [Oppenheimer and Doman] [Oppenheimer and Doman 2006b] [Oppenheimer et al. 2007] [Peng et al. 2014] [Peng et al. 2019] [Platus 1967] [Platus 1978] [Platus 1979] [Platus 1980b] [Platus 1980a] [Problems in control system 1994] [Qi and Bu 2021] [Qian et al. 2008] [Qin et al. 2013] [Qin Changmao et al. 2010] [Raney and Lallman 1991] [Rehman et al. 2009a] [Ren and Yang 2017] [Robinson and Gerwin 2001] [Roenneke and Well 1994] [Roenneke and Well 1995] [Ruimin and Jianguo 2018] [Sachan and Padhi 2018] [Schmidt 1993] [Schoettle et al. 1997] [Shakiba and Serrani 2011] [Shi et al. 2020a] [Shou et al. 2021] [Shuai et al. 2022] [Shuping Tan and Zhibin Li 2010] [Singh et al. 2022a] [Singh et al. 2022c] [Stokes and Lombaerts 2023] [Sun and Xin 2014] [Sun et al. 2017a] [Sun and Yang 2013] [Takahashi and Griffin 2023] [Tao et al. 2016b] [Tao et al. 2017] [Thuruthimattam et al. 2003] [Tieshan et al. 2021] [Vick et al. 2012] [Vinh and Medepalli 1994] [Vogel et al. 2009] [Wang 1963] [Wang et al. 2018d] [Wang et al. 2018b] [Wang et al. 2026c] [Wang et al. 2012b] [Wang and Wang 2020] [Wang and Wu 2017] [Wang and Xia 2022] [Wang et al. 2012c] [Wang et al. 2020a] [Wang et al. 2023d] [Wang et al. 2026g] [Wenkai et al. 2017a] [Wexler and Idan 2026] [White et al. 1961] [Wilcox et al. 2009] [Wiseman and Lopez 2026] [Wray 2008] [Wu and Meng 2016] [Wu et al. 2018] [Wu et al. 2025b] [Xi and Meng 2019] [Xia et al. 2020] [Xu 2015] [Xu et al. 2025b] [Xu and Huang 2018] [Xu et al] [Xu and Tang 2010b] [Xu et al. 2012] [Xu et al. 2014] [Xu and Zhang 2015] [Xue and Haibin 2017] [Yan and Fu 2026] [Yao et al. 2025] [Youssef et al. 2008] [Youssef et al. 2009] [Yu et al. 2014a] [Yu et al. 2019b] [Yu et al. 2014c] [Yulian and Bin 2014] [Zhang and Ding 2023] [Zhang et al. 2012a] [Zhang et al. 2022b] [Zhang et al. 2019c] [Zhang et al. 2022a] [Zhao 2023a] [Zhao and Tang 2015] [Zhen and Fei 2012] [Zhong and Wu 2021] [Zhou 2023] [Zhu et al. 2024a] [Zhu and Huizenga 2004] [Zhu and Liu 2015] [Zifeng et al. 2018] [Zong et al. 2012]
Hypersonic, glide and entry vehicles as designs
Hypersonic, glide and entry vehicles as whole designs, being configuration, multidisciplinary optimisation, thermal and energy management and entry decelerators.
172 records. [Aerodynamic Optimization for Hypersonic 1994] [Ahuja and Hartfield 2009] [Akyurtlu et al. 1989] [Alkaya et al. 2018] [Anderson et al. 1991a] [Ardema 1988] [August 2006] [Babish 1970] [Baker et al. 2004] [Balland et al. 2015] [Baradell and McLellan 1963] [Bardenhagen et al. 1996] [Barz 2026] [Berman 1970] [Bonelli et al. 2011] [Borrelli et al. 1998] [Bose et al. 2013a] [Bowcutt 1992] [Boyd 2024] [Bricker et al. 1989] [Burke and Rumpfkeil 2025] [Cao et al. 2023] [Changbao et al. 2020] [Chapter 12 2013] [Che and Tang 2008] [Chernyi and Gonor 1973] [Clapp et al. 2015] [Courtis and Edwards 1996] [Cui and Yang 2009] [da Cunha Follador et al. 2011] [Dalle and Driscoll 2012] [Deepak et al. 2008] [de Moura and Ribeiro 2026] [Dendy et al. 2026] [Dillman et al. 2013] [Dillman et al. 2010] [Dr. Julia Adams 2023] [Dulikravich and Lee 1990] [Dutta et al. 2025] [Ellinwood 1970] [Elliott 1968] [Fain et al. 2026] [Falempin et al. 1995b] [Ferri et al. 1973] [Forsythe et al. 1961] [Frayssinet 2019] [Fusaro et al. 2019] [Fusaro and Viola 2020] [Fusco et al. 2026] [Gasner et al. 1992] [Gong et al. 2006] [Gong Weijie and Tang shuo 2010] [Goyal et al. 2023] [Graves and Emanuel 1996] [Green] [Green et al. 2013] [Guo et al. 2022b] [Guo et al. 2023d] [Harloff and Berkowitz 1988] [Harloff and Berkowitz 1990] [Heathman and Kelly 1966] [Herrmann et al. 2025] [Hirschel et al. 2025] [Hopkins] [Hughes et al. 2011] [Hughes et al. 2005] [Hunt et al. 1997b] [Volkov 2023] [Hypersonic Reentry 2011] [Ide et al. 1989] [Ingenito 2021a] [Jackson and Taylor 1976] [Jing and Shuo 2008] [Jing and Yuan-pei 2015] [Swihart and Henry 1960] [Johnson 2025] [Johnson et al. 2001] [Joint Conference on Lifting 1960] [Jones and Cesnik 2023] [Jorgensen et al. 1971] [Khairul Habib Pulok and Chakravarty 2021] [Kinney 2006] [Koelle 1989b] [Kuranov and Korabelnikov 2008] [Landon et al. 1994] [Lands 1966] [Lee] [Lee et al. 1998] [Lewis 2010] [Lin et al. 1982b] [Lindell et al. 2006] [Ma et al. 2025a] [Macneal and Kyser 1966] [Maisaia 2023] [Mason 1991] [Mason and Lee 1990] [McDonald and Mavris 2000] [Mehta 1989] [Miele 1962] [Miele and Saaris 1963] [Ming et al. 2017] [Moorhouse and Suchomel 2001] [Moura and Ribeiro 2024] [Nakatani et al. 2009] [Novotny et al. 2024] [Palmer] [Palmer 2020] [Pepper 1968] [Perlini et al. 2026] [Pinnell and Bloetscher 1966] [Pollock and Wild 2024b] [Powering the Future 2022] [Pratap Singh et al. 2021] [Priyamvada et al. 2015] [Pulok and Chakravarty 2020] [Qi et al. 2025] [Qin et al. 2008] [Ren 2009] [Research and Technology Organisation 2005] [Bodkin et al] [Rodriguez-Segade et al. 2020] [Rodríguez-Segade et al. 2022] [Rodríguez-Segade et al. 2024] [Rodriguez-Segade Alonso et al. 2021] [Roth and Mavris 1999] [Ruble 1964] [Sforza 2019] [Shaw and Porter 2006] [Sheffer and Dulikravich 1993] [Shen et al. 2020] [Sheta et al. 2015] [Shope 1991] [Shope and Spinetti 1993] [Simon et al. 2021] [Sivasubramanian et al. 2026b] [Sonic Boom Analysis 1975] [Stadler 1993] [Stubbe 1990] [Suzuki 2016] [Swanson et al. 2015] [Thibodeaux 2002] [Gregory et al. 1964] [Tianyang et al. 2024] [Tracy and Wright 2020] [Ueno et al. 2011] [Vangriethuysen and Wallace 1993] [Wall 1964] [Wang and Gao 2013] [Wang et al. 2019g] [Wang et al. 2025i] [Wang et al. 2023e] [Wang et al. 2025k] [Wang et al. 1980] [Wenkai et al. 2017b] [Bastedo 2021b] [Williams et al. 2024] [Woodyard 2026] [Wright 2015] [Xiong et al. 2021] [Xu et al. 2025c] [Yamada et al. 2011] [Yamada et al. 2013] [Yan et al. 2008] [Yang 2025] [Yin et al. 2024a] [Yin et al. 2025] [Zhang et al. 2023d] [Zhang et al. 2016b] [Zhang et al. 2024b] [Zhang et al. 2025f] [Zou et al. 2024] [Zweber et al. 2002]
Hypersonic research programmes, reviews and histories
National and international hypersonic research programmes, technology reviews and histories of the field, which are the company the X-60A’s programme keeps.
45 records. [Advisory Group for Aerospace Research and Development 1997] [Anderson 1987] [Ayers 1990] [Blankson and Pyle 1993] [Bogdonoff 1999] [Burns 2020] [ChoHee Kim et al. 2021] [Continuing to Push 2006] [Cummings 2022] [Dietrick 2013] [Douglas and Lindgren 1999] [Fetterhoff et al. 2006b] [Kirkham et al. 1975] [Guizzo 2004a] [Gurijanov and Harsha 1996] [Hallion 1998] [Heo and Ryu 2025] [Houchin 2006] [Hypersonic Flight 2025] [Johnston and Sawyer 1988] [Khambaswadkar 2024] [Kong et al. 2023] [Kostoff et al. 2003] [Krause 1992] [Lees and Kubota 1972] [Lewis and Paull 1998] [Lu et al. 2018] [Maita and Kobayashi 1996] [Melville and Helmich 2021] [Mercier and Ronald 1998] [Review and Evaluation 1998] [Sabo et al. 1987] [Sancho 1993] [Sancho and Colin 1995] [Schwelkart and Hallion 1997] [Sochor 1991] [Speer and Hoyt 1988] [Stollery 1972] [Supersonic and Hypersonic Flight 1960] [Swihart 1992] [The Quest for Hypersonic 2011] [Vert and Bouchard 2024] [Wegener 1997] [Wright and Tracy 2024] [Zuber and Bertin 1998]
The atmosphere and the flight condition
The standard atmosphere itself, which every altitude-dependent number in this article passes through, with the meteorological rocket soundings and range reference atmospheres that measured the layers the corridor sits in.
141 records. [A 2006] [Adelfang et al. 1993] [Adelfang 2004] [Air Force Test Pilot School Edwards Afb Ca 1962] [Appendix a. the Standard 2011] [Appendix a Standard Atmosphere 2021] [Appendix B 2003] [Aufm Kampe and Lowenthal 1963] [B-34. U. S. Standard 1963] [Bass et al. 2007] [Bauman et al. 1992] [Beer and Lennox 1965] [Belmont 1985] [Bettle et al. 1967] [Bieber 1966] [Bieber 1967] [Blanchet et al. 2001] [Briggs 1965] [Brown 2012] [Burns et al. 2008] [Callus 1969] [Callus 1971] [Clark 1965] [Cochran and Duncan 1966] [Data Report 1966] [Dean 1979] [Decker et al. 2008] [Decker et al. 2015] [Definition of the Standard 1954] [Duvall et al. 2005] [Eckermann et al. 1995] [Essenhigh 2006] [Everett et al. 1972] [Experimental InterAmerican Meteorological Rocket 1970] [Finger and Woolf 1967b] [Finger and Woolf 1967a] [Galeriu 2022] [Geng et al. 2022] [Giraytys and Rippy 1964] [Giraytys and Rose 1966] [Griffith 1961] [He et al. 2025a] [Hedin 1988] [Henry and Quiroz 1970] [Herbert] [Justh] [Justh et al] [Hodur 1997] [Hyman and Shi 1994] [ICAO Standard Atmosphere 2021] [International Standard Atmosphere 2010] [International Standard Atmosphere ISA 2017] [Jenkins et al. 1960] [Jiang et al. 2011b] [Johnson et al. 2002] [Justus 1988] [Justus et al. 2004] [Justus and Johnson 1990] [Justus et al. 1976] [Justus and Roper 1987] [Kampe 1960] [Kaushik 2018] [Kingwell et al. 1991] [Kirtskhalia 2012] [Kirtskhalia 2021] [König et al. 2019] [Kumar 2025] [Kurzke and Halliwell 2018] [Kurzke et al. 2025] [Li et al. 2017f] [McCarty 1987] [Merrill et al. 1982] [Miller 1969b] [Miller et al. 1968] [Morgan and Collins 1962] [Morrissey and Carten 1967] [Narayanan 1976] [Newell 1963] [Nordberg and Smith 1964] [Nordberg and Warnecke 1965] [Other Publications 1987] [Ouseph and Link 1984] [Peters 1977] [Pinier 2024] [Pressures and Temperatures 2000] [Properties of the U.S. 2014] [Properties of the U.S. 2024] [White and Hoffman 2021] [Quiroz 1967] [Quiroz 1972] [Rao 1967] [Report No. 538 Altitude-Pressure 1935] [Roble 2000] [Rocket and Satellite Meteorology. 1963] [Rodman 1991] [Rotolante and Parra 1965] [Schmidlin 2000] [Schmidlin et al. 2010] [Science Communication INC Mclean VA 1960] [Shi et al. 2011b] [Shimizu 1972] [Sissenwine 1963] [Smith and Galusha 1983] [Space environment natural and] [National Bureau of Standards 1927a] [National Bureau of Standards 1927b] [Standard Atmosphere Data 1992] [Standard Atmosphere 1997] [Standard Atmosphere 2005] [Standard Atmosphere Data 2013] [Standard Atmosphere 2023] [Standard Atmosphere 2024] [Standard Atmospheric Profilesa aSource 2002] [Stroud 1958] [Taheri 2013] [Teweles 1964] [The Flight Environment 2021] [The International Standard Atmosphere 2017] [The International Standard Atmosphere 2026] [The Meteorological Rocket Network-An 1961] [The Standard Atmosphere 1964] [The Standard Atmosphere 1976] [Thiele 1963] [Thorp and Kapel 2006] [Tingle 1983] [Turns and Kraige] [U.S.Committee on Extension to the Standard Atmosphere 1966] [1976 US Standard Atmosphere 2014] [Vaquero et al. 2004] [Vaughan 2003] [Webb 1968] [Webb et al. 1966] [Webb et al. 1961] [Webb and Jenkins 1959] [White 2026a] [White 2017a] [White 2017b] [Winchell 1992] [Worland and Wilson 1999] [Yager 2013] [Yang and Wu 1982]
Where the Framing Breaks Down
Reading the X-60A as an X-plane misleads in three ways, and this article examines the third at greatest length.
It suggests a research question, and there was not one. Every other vehicle in this series was built to find something out. This one was built to sell a service, and its technical content is entirely in the delivery of a condition rather than in the answering of a question. Judging it by what it discovered is judging a wind tunnel by what it discovered.
It suggests a flight test programme, and the appropriate comparison is a facility procurement. A wind tunnel that is ordered, designed, built and then never commissioned is a familiar kind of failure with a familiar accounting. It is not usually written up as an aeroplane that never flew.
And it suggests that calling the vehicle an aircraft was a slip. It was not. The X series is defined over aircraft by the instruction that governs it, so the only way for a research rocket to enter the series is for the paperwork to call it an aircraft, and the paperwork duly did. The error, if there is one, is in the taxonomy having no research category for anything that is not an aeroplane, which traces to a designator format established in 1962 and restated in a 2020 instruction [DAFI 16-401] rather than to anyone’s carelessness.
There is also a limit on how far the physics in this article should be pushed. The trajectory is a demonstration and not a reconstruction. No trajectory appears in the programme’s releases, the drag coefficient is generic, the specific impulse is assumed, and the thrust used is a sea-level rating for a vehicle that never sees sea level. The conclusions that survive those uncertainties are the qualitative ones, being that the corridor is a choice rather than a limit, that cruise requires throttling at the edge of the art, that the statutory inequality is satisfied by a wide margin, and that the dwell above Mach 5 is measured in seconds rather than minutes. The specific figures should be read as order-of-magnitude statements with their assumptions attached.
The Source Base
75 hand-written references carry the argument and 9,694 research records map the field, and this article keeps them apart on purpose. The claims about what a document does and does not say rest on documents read in full, being the register, the instruction that governs it, three Air Force releases, two sections of the United States Code and the federal contract record. Those are not commentary on the evidence. They are the evidence.
The research records are bibliographic records rather than documents read in full, drawn from Crossref, from the Technical Reports Server of the National Aeronautics and Space Administration and from the Defense Technical Information Center. Of the 9,694 records, 742 are Technical Reports Server citations and 8,952 are Digital Object Identifiers, 700 of them registered by the Defense Technical Information Center under the prefix 10.21236.
The cited references dated no later than 2026 span 1924 to 2026 with a median publication year of 2007, measured over the 9,424 records whose year the index supplies, less 2 that it dates 2027.
The Definition of Primary
1,442 of the 9,694 research references are report primaries, which is 14.9 percent. A report primary here is a record whose identifier is a citation on the space agency’s Technical Reports Server or a Digital Object Identifier registered by the defence technical information centre under the prefix 10.21236, both of which publish original work rather than commentary on it. The test is applied to the identifier and not to the title, so the share is a lower bound on the original work the survey holds, since journal and conference papers that report original work are not counted as primaries.
75 references are hand-written and read in full. Three works are not cited directly. A general reference work on this series is a 2021 Springer volume whose title ends at this very vehicle. It holds an Open Library work record, OL25805288W, and the Digital Object Identifier 10.1007/978-3-030-86398-2, and it is named through the registry that cites it rather than cited directly. Regan’s re-entry dynamics and Hankey’s re-entry aerodynamics are not cited because the library index returns nothing for them on title and author.
Thin Subjects
Eight subjects that this article’s derivations depend on have thin literatures in this survey, counted over the titles of the 9,694 research records. A title counts when it carries a term from every group in its row, and the groups are separated by the word with.
| Subject | Title terms | Titles |
|---|---|---|
| two-body orbital mechanics of the burnout state | Keplerian, vis-viva, orbital element, orbital elements, two-body, orbital mechanics | 0 |
| the vacuum instantaneous impact point | instantaneous impact point, instantaneous impact points | 1 |
| the designation of military aerospace vehicles | designation, designations, designator, designators | 0 |
| the pressure scale height of the atmosphere | scale height, scale heights | 0 |
| the recovery factor of a boundary layer | recovery factor, recovery factors, recovery temperature, adiabatic wall | 1 |
| deep throttling of a liquid rocket engine | deep throttling, deeply throttled | 18 |
| injector stiffness under throttling | injector, injectors with stiffness, pressure drop, throttling, throttleable | 7 |
| the air-launched liquid rocket | air-launched, air-launch, air launching with liquid | 1 |
One of this article’s conclusions is not supported by its own survey, and that is a decision rather than an oversight. The statutory suborbital test rests on two-body orbital mechanics, and the survey excludes astrodynamics on purpose, because orbit is the worst homonym in the vehicle’s own name and admitting it would bring the whole of spaceflight into a survey of endoatmospheric flight. None of the 9,694 research references carries Keplerian, vis-viva, orbital element, two-body or orbital mechanics in its title.
That conclusion is carried by the textbooks rather than by the survey, and the article says so here rather than leaving a reader to infer from a citation count that the question is unstudied. A survey that excludes a subject has not measured it. The vacuum instantaneous impact point, which decides the second half of the statutory test, appears in 1 title, as a range-safety constraint on a launch vehicle’s trajectory [Yoon and Ahn 2016].
No title in the survey names the designation of a military aerospace vehicle, so the section headed Aircraft to the Register, Rocket to the Statute rests on the instruction and the register alone. The pressure scale height, which governs how hard the corridor is to hold, appears in no title either, and the recovery factor that corrects a stagnation temperature to a wall temperature appears in 1 [Nicoll 1963]. Both are textbook relations, and the article evaluates them rather than citing a measurement of them.
Deep throttling, on which the section headed Can the Condition Be Held turns, is named in 18 titles, and 7 titles name an injector together with stiffness, pressure drop or throttling. Eight of the 18 deep-throttling titles name a hydrogen or cryogenic engine and none names kerosene or another hydrocarbon, and only 2 titles pair throttling with liquid oxygen and kerosene at all, so the throttling the corridor table asks of the Hadley, a liquid oxygen and kerosene engine, is thin even by the standards of this subsection. The air-launched liquid rocket itself, which is what the X-60A was, is named in 1 title, an analysis of propellant slosh [Coogan and Musgrove 2017].
What the Survey Admits
A record is admitted only when a person reading its title finds it on this article’s subject, which is the vehicle and the vehicles it is measured against, air launch, the corridor and the trajectory inside it, the engine, the air-breathing payloads, the heat, the ground and flight test of the condition, the rules a rocket flies under, the cost of a flight test, the flight dynamics of slender rockets and hypersonic vehicles, sounding rockets, launch vehicles and the atmosphere the corridor is drawn in. The clusters in The Contemporary Literature divide the admitted records by topic. No cluster is a residual, because the same reading assigns every admitted record to a named cluster, and a record that fits no named cluster is not admitted.
Every proper noun in this vehicle’s parts list collides with a large literature, and the admission rule excludes those collisions. The engine is the Hadley, which in atmospheric science is a circulation cell and a research centre. Its maker is Ursa Major, a constellation with a photometric literature older than aviation. The carrier is a Gulfstream, which is an ocean current. The contractor is Generation Orbit, and orbit is an electron shell, an eye socket, a periodic solution of a dynamical system and the whole of astrodynamics.
The less obvious collisions are with the vocabulary of the subject itself. Sandia’s PEGASUS is a capacitor bank that accelerates flyer plates, and it shares its name with the air-launched booster against which many studies in this survey measure themselves. The word booster is what hides it, because a pulsed-power flyer plate is called a booster projectile, so the title carries launch vocabulary throughout. The Black Brant is a goose as well as a sounding rocket, Pegasus is a winged horse as well as a booster, and trajectory, payload and flight corridor are equally the words of small drones, robotics and pedestrian traffic. Papers on lightning triggered by small rockets share the word rocket and nothing else. The admission rule excludes those classes, together with correction, erratum, retraction and withdrawal notices, which are not works. A review of a book, a short dictionary or reference entry, an editorial or a news notice and a second deposit of the same document are not admitted either, because none of them is a further research work.
The reading also excludes records whose only link to the subject is a distant application of the same vocabulary. Those are rocket-borne science whose subject is the science, such as auroral, ionospheric and astronomical measurements, spacecraft and in-space propulsion including nuclear and electric rockets, missile defence policy and strategy, artillery and tactical rocket ordnance as logistics, packaging or inspection, propellant chemistry and motor case manufacture, conventional aircraft and helicopters whose own test programme is the subject, drones, balloons and airships, the atmospheres of other planets, weather and climate models, and news items.
Some records are kept although their subject is adjacent rather than central, and the reason in each case is a fact about the subject. The meteorological rocket literature is kept because a meteorological rocket is a sounding rocket, which is this vehicle’s direct ancestor, and because it measured the layers the corridor sits in. The environmental assessments written for launches and hypersonic flight tests are kept because they are the regulatory documents for exactly this kind of flight. Ascent and landing trajectories of rockets on the Moon and Mars are kept as rocket trajectory optimisation, entry heating and thermal protection for other planets as aerothermodynamics and thermal protection, the deep-throttling engines of lunar landers because throttling is the subject of the section headed Can the Condition Be Held, and the guidance and aerodynamics of artillery rockets as the flight dynamics of finned rockets.
Every research title has been read for relevance, so the off-topic share that remains is a matter of reading judgement. A document deposited twice on the same report server under one title is cited once.
Epistemic State
Historical fact, from primary documents. The designation X-60A was allocated on 07-Sep-18 to Generation Orbit Launch Services with the Air Force as sponsor [Parsch, DOD 4120.15-L Addendum]. The Air Force announced it on 4 October 2018, describing an air-dropped liquid rocket powered by the Hadley engine and providing access to conditions between Mach 5 and Mach 8, and stating that this was the first Air Force Small Business Innovation Research programme to receive an X designation [Air Force]. Critical design review completed and was announced on 7 March 2019 with first flight expected in about a year from Cecil Spaceport [AFRL]. Integrated propulsion verification testing including cold flow and hot fire completed and was announced on 15 January 2020 [AFRL]. Contract FA865017C2414 ran from 2017-03-27 to 2023-02-28 and obligated 30,921,064.62 dollars across 30 modifications [USAspending]. The Hadley engine first flew on 9 March 2024 on Stratolaunch’s Talon-A1 [Ursa Major].
Historical fact, from a secondary source that names its own limits. Three captive-carry flights of full-scale inert vehicles were complete by December 2017, and in February 2020 the Air Force Research Laboratory deferred the first flight from March to later that year without stating a reason [Directory of U.S. Military Rockets and Missiles]. That source also records that no further news items about the X-60A appear after February 2020.
Engineering analysis, computed here and reproducible from the published inputs. Dynamic pressure is $\tfrac{1}{2}\gamma p M^2$ with temperature cancelled, so Mach 5 at 21,300 metres is 1,649 pounds per square foot. At the corridor altitude the scale height is 6,378 metres and dynamic pressure changes 14.51 percent per kilometre at fixed Mach. Stagnation temperature at Mach 8 on the 1,500 pound per square foot line is 3,099 kelvin with a stagnation pressure ratio of 9,762.9. The thrust-to-weight ratio at release on the rated sea-level thrust is 1.668.
Engineering analysis resting on stated assumptions. The booster diameter of 0.501 metres is recovered from the propellant volume, assuming a mixture ratio of 2.3 to 1, seventy percent tankage occupancy and cylindrical tanks at full body diameter. The propellant fractions of 43.8, 50.5 and 62.7 percent for Mach 5, 6 and 8 assume a specific impulse of 290 seconds, which is not published for this engine, and a generic slender-body drag coefficient. The trajectory is a demonstration of what the published corridor costs and not a reconstruction of any planned flight.
Inference, stated as such. That the money moving from flight testing to numerical analysis in May 2020 marks the point at which the programme stopped expecting to fly is an inference from a purchase description and is not stated anywhere. That the Hadley engine’s qualification in 2021, a year after the planned first flight, contributed to the deferral is an inference from a date and is not stated anywhere. Neither is asserted as fact and neither should be repeated as one.
What the record does not settle. Whether the X-60A was ever cancelled, and by whom, and when. Whether it ever flew. Whether the 3.07 years of contract after February 2020 bought hardware, analysis, storage or a wind-down. What the equipment shipped in December 2022 was, and where it went. Whether an FAA launch licence was ever applied for or issued, and whether the government-for-government exemption at 51 U.S.C. 50919 would have applied. What the Hadley’s specific impulse and throttle range are. Whether the X-60C exists as anything more than a name on a list of past projects.
The bibliography reaches past the dateline and the body does not. The reference survey in The Contemporary Literature includes work published after the editorial date of 5 December 2025, as the span stated in The Source Base shows, because a survey of a field is written from current knowledge. No event later than the editorial date is asserted in the body. Where a fact postdates the dateline it appears in the bibliography and not in the narrative.
Engineering analysis over a family of trajectories. The published pair of Mach 5 and seventy thousand feet is a reachable flight condition for a vehicle of this thrust-to-weight ratio. Across 53 pitch programmes the vehicle reaches Mach 5 anywhere between 55.7 and 147.9 thousand feet, spanning a factor of 72.8 in dynamic pressure, with the published pair sitting unremarkably inside. The result depends on the family being wide, because a narrow family of pitch programmes can miss the published pair altogether.
Engineering analysis solved as a fixed point. The propellant load and the recovered diameter are not independent, because the volume sets the diameter, the diameter sets the drag, and the drag sets the propellant. Solved as the fixed point it is, the recovered diameter comes out 8.2 percent larger than a single sequential pass gives.
Out of Scope
The scramjet, thermal protection and autonomous control payloads the X-60A was to carry are named in the designation release and are not treated here, because none was flown on it and each has a literature of its own. The X-43 and the X-51 carry the air-breathing flight test story in this series.
The Stratolaunch Talon-A, which flew the Hadley engine and occupies much of the mission space the X-60A was built for, is a separate vehicle with a separate designation history and is mentioned here only where the engine connects them.
Air launch as a route to orbit, as distinct from air launch as a route to a test condition, is a large and separate subject. The Pegasus booster appears throughout the reference survey in The Contemporary Literature and is not analysed.
The detailed regulatory history of commercial launch licensing under 14 CFR Part 450 and its predecessors is named where it bears on which regime would have governed an X-60A flight and is not otherwise developed.
Conclusion
The X-60A was a rocket that the designation system had to call an aircraft in order to give it a number, and it never flew.
Both halves of that sentence are established from documents. The Air Force’s own releases call the vehicle a rocket 12 times in 1,032 words and call it an aircraft 1 time, and that once refers to the carrier. The register calls it an aircraft, and the instruction that governs the register explains why it had no alternative, because the X in an X number is the Research basic mission and the Research basic mission is defined over aircraft. The rocket system’s X is only a status prefix, so a vehicle designated as a rocket cannot be an X-plane at all.
The physics underneath the programme is a single relation. Dynamic pressure is $\tfrac{1}{2}\gamma p M^2$, the temperature cancels, and the two figures the Air Force published are therefore not a speed and a ceiling but a test condition of 1,649 pounds per square foot. The vehicle’s virtue was that this condition was a choice rather than a limit, reachable across a factor of 72.8 in dynamic pressure by changing a pitch programme rather than hardware. In that sense a flying wind tunnel is a wind tunnel. Its difficulty was that a burning rocket accelerates, so the time above Mach 5 is the tail of the burn, around 12.2 seconds on the integrated trajectory, and holding a steady condition instead would demand throttling to between 5.2 and 20.9 percent, which is at or past the edge of the art.
Federal law asked the one question about this vehicle whose answer is a verdict rather than a measurement, and it asked it in a form that has to be computed. A suborbital rocket is one whose thrust exceeds its lift for the majority of powered ascent, and across every pitch programme tested the thrust exceeds the lift for 100 percent of it, with the largest lift demanded anywhere reaching 0.591 of the thrust.
The programme reached its last reported milestone before flight and stopped. Full-duration burns, gimballing and throttling were demonstrated on the ground in January 2020, the first flight moved in February, and nothing was published afterwards. The contract ran another 3.07 years and spent 30.1 percent of its money in that time, redirecting 4,808,000 dollars into numerical analysis three months after the deferral and closing with 22,873.11 dollars to ship the equipment.
The engine flew. Four years after the month in which the X-60A was to have made its first flight, the Hadley lit on Stratolaunch’s Talon-A1. The condition the X-60A was built to sell is now sold by somebody else, from a different airframe, without a number from the X series.
And the cost per second of hypersonic condition delivered by the X-60A remains undefined, because the programme’s own figure of merit has a denominator, and the denominator is zero.
Equations
This section collects the 79 display equations of the article in the order they appear, each under its number and reproduced exactly as it stands in the text. A title in bold names an established result, and a title in italics beginning with the word Bespoke names a construction made for this analysis. Of the 79, 62 are established and 17 are bespoke. Pressures are in pascals except where the published dynamic pressure is quoted in pounds per square foot, speeds are in metres per second, masses in kilograms, thrusts in newtons and costs in dollars, altitudes are geometric or geopotential as the symbol table distinguishes, and every figure taken from the integrated ascent rests on a commanded pitch programme, an interpolated drag coefficient and an assumed specific impulse rather than on a published trajectory.
Equation 1, Inlet Air Mass Flow. The mass flow an inlet of given capture area swallows is the density times the speed times the area, or twice the dynamic pressure over the speed times the area.
\[\dot{m}_a \;=\; \rho V A_c \;=\; \frac{2 q}{V} \, A_c \tag{1}\]Equation 2, Bespoke Captured Mass Flux at Mach 6 Mid-Band. The mass flux per unit capture area is evaluated at 1,500 pounds per square foot, the midpoint the article takes of the one to two thousand band, with the Mach 6 speed scaled from the Mach 5 corridor speed.
\[\frac{\dot{m}_a}{A_c} \bigg|_{M = 6} \;=\; \frac{2 \times 1500 \times 47.88\ \text{Pa}} {1,479.5\ \text{m/s} \times 6/5} \;=\; 80.9\ \text{kg}\,\text{m}^{-2}\text{s}^{-1} \tag{2}\]Equation 3, Transition Reynolds Number. Boundary-layer transition depends on a Reynolds number based on the distance from the leading edge.
\[\mathit{Re}_x \;=\; \frac{\rho V x_t}{\mu} \tag{3}\]Equation 4, Wall-to-Recovery Temperature Ratio. Transition also depends on the ratio of the wall temperature to the temperature an insulated wall would reach.
\[\frac{T_w}{T_r} \tag{4}\]Equation 5, Dynamic Pressure. The dynamic pressure is half the density times the square of the true airspeed.
\[q = \tfrac{1}{2} \rho V^2 \tag{5}\]Equation 6, Perfect Gas Law. For a perfect gas the density is the pressure over the gas constant times the temperature.
\[\rho = \frac{p}{R T} \tag{6}\]Equation 7, Speed of Sound and True Airspeed. The speed of sound depends on temperature alone, and the true airspeed is the Mach number times that speed.
\[a = \sqrt{\gamma R T}, \qquad V = M a \tag{7}\]Equation 8, Dynamic Pressure in Terms of Pressure and Mach Number. Substituting the gas law and the speed of sound cancels the temperature, leaving half the ratio of specific heats times the pressure times the square of the Mach number.
\[q \;=\; \tfrac{1}{2} \rho V^2 \;=\; \tfrac{1}{2} \left( \frac{p}{R T} \right) \left( \gamma R T \right) M^2 \;=\; \tfrac{1}{2} \gamma p M^2 \tag{8}\]Equation 9, Working Form of Dynamic Pressure for Air. With a ratio of specific heats of 1.4 the dynamic pressure is 0.7 times the pressure times the square of the Mach number.
\[q \;=\; 0.7 \, p \, M^2 \tag{9}\]Equation 10, Pressure From Dynamic Pressure and Mach Number. Inverting the working form gives the ambient pressure that a dynamic pressure and a Mach number fix.
\[p \;=\; \frac{2 q}{\gamma M^2} \tag{10}\]Equation 11, Dynamic Pressure of the Published Test Condition. Mach 5 at the published altitude of seventy thousand feet, where the standard atmosphere gives 4,512.9 pascals, corresponds to a dynamic pressure of about 1,649 pounds per square foot. Heiser and Pratt Anderson
\[q \;=\; \tfrac{1}{2} \times 1.4 \times 4,512.9\ \text{Pa} \times 5^2 \;=\; 78,976\ \text{Pa} \;=\; 1,649\ \text{lbf/ft}^2 \tag{11}\]Equation 12, Hydrostatic Equation. The pressure gradient with altitude is minus the gravity times the density, or with the gas law minus the gravity times the pressure over the gas constant times the temperature. U.S. Standard Atmosphere 1976 1976
\[\frac{dp}{dh} = -\, g \rho = -\, \frac{g p}{R T} \tag{12}\]Equation 13, Geopotential Altitude. Geopotential altitude folds the variation of gravity into the altitude coordinate through the effective Earth radius. U.S. Standard Atmosphere 1976 1976
\[h = \frac{R_e \, z}{R_e + z} \tag{13}\]Equation 14, Piecewise Linear Temperature Profile. In the standard atmosphere the temperature is linear in geopotential altitude within each layer.
\[T(h) = T_b + \lambda \, (h - h_b) \tag{14}\]Equation 15, Pressure in a Layer With Nonzero Lapse Rate. Integrating the hydrostatic equation through a layer with a nonzero lapse rate gives a power law in the temperature ratio.
\[p(h) \;=\; p_b \left[ 1 + \frac{\lambda \, (h - h_b)}{T_b} \right]^{-g_0 / (R \lambda)} \qquad (\lambda \neq 0) \tag{15}\]Equation 16, Pressure in an Isothermal Layer. Through an isothermal layer the pressure decays exponentially with geopotential altitude. International Standard Atmosphere
\[p(h) \;=\; p_b \, \exp\!\left[ -\, \frac{g_0 \, (h - h_b)}{R \, T_b} \right] \qquad (\lambda = 0) \tag{16}\]Equation 17, Pressure Scale Height. The scale height is the gas constant times the temperature over standard gravity. International Standard Atmosphere
\[H = \frac{R T}{g_0} \tag{17}\]Equation 18, Altitude Sensitivity of Dynamic Pressure at Fixed Mach Number. At fixed Mach number the dynamic pressure inherits the pressure’s logarithmic gradient, minus one over the scale height.
\[\frac{1}{q} \frac{\partial q}{\partial z} \bigg|_{M} \;=\; \frac{1}{p} \frac{dp}{dz} \;=\; -\, \frac{1}{H} \tag{18}\]Equation 19, Finite Change of Dynamic Pressure per Kilometre. At the 6,378 metre scale height of the corridor altitude a kilometre of climb removes 14.51 percent of the dynamic pressure.
\[\frac{\Delta q}{q} \;=\; 1 - \exp\!\left( -\, \frac{\Delta z}{H} \right) \;=\; 14.51\ \text{percent per kilometre} \tag{19}\]Equation 20, Slope of a Constant Dynamic Pressure Line. Along a line of constant dynamic pressure the logarithm of the Mach number rises with altitude at one over twice the scale height.
\[\frac{d(\ln M)}{dz} \bigg|_{q} \;=\; \frac{1}{2H} \tag{20}\]Equation 21, Stagnation Temperature Ratio. The energy equation for a perfect gas gives the stagnation temperature ratio as one plus half of one less than the ratio of specific heats times the square of the Mach number.
\[\frac{T_0}{T} \;=\; 1 + \frac{\gamma - 1}{2} M^2 \tag{21}\]Equation 22, Stagnation Enthalpy. The stagnation enthalpy per unit mass is the specific heat at constant pressure times the stagnation temperature.
\[h_0 = c_p T_0 \tag{22}\]Equation 23, Isentropic Stagnation Pressure Ratio. The stagnation pressure ratio follows from the isentropic relation.
\[\frac{p_0}{p} \;=\; \left( 1 + \frac{\gamma - 1}{2} M^2 \right)^{\gamma / (\gamma - 1)} \tag{23}\]Equation 24, Recovery Factor. The recovery factor is the square root of the Prandtl number in a laminar boundary layer and its cube root in a turbulent one.
\[r_f \;=\; \mathit{Pr}^{1/2} \;\; \text{(laminar)}, \qquad r_f \;=\; \mathit{Pr}^{1/3} \;\; \text{(turbulent)} \tag{24}\]Equation 25, Adiabatic Wall Recovery Temperature. The recovery temperature applies the recovery factor to the stagnation temperature rise. Anderson Bertin
\[T_r \;=\; T \left( 1 + r_f \, \frac{\gamma - 1}{2} M^2 \right) \tag{25}\]Equation 26, Sutherland’s Law. Sutherland’s law gives the viscosity of air as a function of temperature.
\[\mu = \frac{C_1 \, T^{3/2}}{T + S_u} \tag{26}\]Equation 27, Reynolds Number. The Reynolds number is the density times the speed times a reference length over the viscosity.
\[\mathit{Re} = \frac{\rho V L_r}{\mu} \tag{27}\]Equation 28, Unit Reynolds Number. The unit Reynolds number is the Reynolds number per metre of length, reported when the test article length is not fixed.
\[\frac{\mathit{Re}}{L_r} \;=\; \frac{\rho V}{\mu} \tag{28}\]Equation 29, Sutton-Graves Stagnation-Point Heating. The convective heat flux at a stagnation point scales as the square root of density over nose radius and the cube of velocity. Atmospheric entry Vinh, Busemann and Culp
\[\dot{Q} \;=\; k_s \sqrt{\frac{\rho}{R_n}} \; V^3 \tag{29}\]Equation 30, Rocket Thrust. Rocket thrust is the momentum flux of the jet plus the pressure difference at the exit plane times the exit area.
\[F = \dot{m} \, v_j + \left( p_e - p_a \right) A_e \tag{30}\]Equation 31, Effective Exhaust Velocity and Specific Impulse. The effective exhaust velocity is thrust over mass flow, and the specific impulse is that velocity over standard gravity.
\[v_e = \frac{F}{\dot{m}}, \qquad I_s = \frac{F}{\dot{m} \, g_0} \tag{31}\]Equation 32, Characteristic Velocity and Thrust Coefficient. The thrust separates into the characteristic velocity of the chamber and the thrust coefficient of the nozzle.
\[c_* = \frac{p_c A_t}{\dot{m}}, \qquad C_F = \frac{F}{p_c A_t}, \qquad F = \dot{m} \, c_* \, C_F \tag{32}\]Equation 33, Nozzle Area Ratio. The nozzle area ratio is the exit area over the throat area.
\[\epsilon = \frac{A_e}{A_t} \tag{33}\]Equation 34, Isentropic Area-Mach Relation for the Nozzle. The area ratio and the exit Mach number of a convergent-divergent nozzle are related through the isentropic area-Mach relation.
\[\epsilon \;=\; \frac{A_e}{A_t} \;=\; \frac{1}{M_x} \left[ \frac{2}{\gamma + 1} \left( 1 + \frac{\gamma - 1}{2} M_x^2 \right) \right]^{(\gamma + 1) / (2(\gamma - 1))} \tag{34}\]Equation 35, Choked Mass Flow Through a Throat. The mass flow through a choked throat is set by the chamber pressure, the throat area and the chamber temperature through the Vandenkerckhove function.
\[\dot{m} \;=\; \frac{\Gamma \, p_c A_t}{\sqrt{R \, T_c}}, \qquad \Gamma \;=\; \sqrt{\gamma} \left( \frac{2}{\gamma + 1} \right)^{(\gamma + 1) / (2(\gamma - 1))} \tag{35}\]Equation 36, Bespoke Product of Chamber Pressure and Throat Area. Taking a characteristic velocity of 1,800 metres per second, a typical value the article assumes because none is published for this engine, gives the product of chamber pressure and throat area from the mass flow alone.
\[p_c A_t \;=\; \dot{m} \, c_* \;=\; 14,078\ \text{N} \tag{36}\]Equation 37, Altitude Variation of Rocket Thrust. With a fixed nozzle the thrust rises from its sea-level value toward the vacuum thrust as the ambient pressure on the exit area falls. Ursa Major
\[F(z) \;=\; F_v - p(z) \, A_e, \qquad F_v = F(0) + p_b(0) \, A_e \tag{37}\]Equation 38, Thrust-to-Weight Ratio at Release. The published sea-level thrust of 5,000 pounds against the published gross mass of 1,360 kilograms gives a thrust-to-weight ratio of 1.668. Directory of U.S. Military Rockets and Missiles Ursa Major
\[\frac{F}{W} \;=\; \frac{22,241\ \text{N}}{13,337\ \text{N}} \;=\; 1.668 \tag{38}\]Equation 39, Bespoke Kinematic Velocity Increment With Climb. The article counts the climb as velocity through its potential energy, taking the increment as the speed whose kinetic energy equals that of the corridor plus the climb, less the release speed.
\[\Delta V_k \;=\; \sqrt{ V^2 + 2 g_0 \, \Delta z } \; - \; V_0 \tag{39}\]Equation 40, Bespoke Kinematic Increment From Release to the Corridor. The increment is evaluated from a release at twelve kilometres and Mach 0.8, a release condition the article takes, to the Mach 5 corridor 9,300 metres higher. Directory of U.S. Military Rockets and Missiles
\[\Delta V_k \;=\; \sqrt{ (1,479.5)^2 + 2 \times 9.80665 \times 9,300 } \; - \; 236.1 \;=\; 1,303.9\ \text{m/s} \tag{40}\]Equation 41, Velocity Increment Including Gravity and Drag Losses. The velocity increment the rocket must supply is the kinematic increment plus the integrated gravity and drag losses.
\[\Delta V \;=\; \Delta V_k + \Delta V_g + \Delta V_d, \qquad \Delta V_g = \int_0^{t_b} g \sin\theta \; dt, \qquad \Delta V_d = \int_0^{t_b} \frac{D}{m} \; dt \tag{41}\]Equation 42, Tsiolkovsky Rocket Equation. The rocket equation converts a velocity increment into the logarithm of the mass ratio through the effective exhaust velocity.
\[\Delta V \;=\; I_s \, g_0 \, \ln\!\left( \frac{m_0}{m_f} \right) \tag{42}\]Equation 43, Mass Ratio and Propellant Fraction. Inverting the rocket equation gives the mass ratio and the propellant fraction that a velocity increment demands.
\[\frac{m_0}{m_f} \;=\; \exp\!\left( \frac{\Delta V}{I_s g_0} \right), \qquad \zeta \;=\; \frac{m_p}{m_0} \;=\; 1 - \exp\!\left( -\, \frac{\Delta V}{I_s g_0} \right) \tag{43}\]Equation 44, Vehicle Mass Budget. The ignition mass is the sum of the propellant, the structural and inert mass and the payload.
\[m_0 = m_p + m_s + m_l \tag{44}\]Equation 45, Propellant Mass Flow and Burn Duration. The mass flow is thrust over specific impulse times standard gravity, and the burn duration is the propellant mass over that flow.
\[\dot{m} = \frac{F}{I_s \, g_0}, \qquad t_b = \frac{m_p}{\dot{m}} \tag{45}\]Equation 46, Bespoke Hand-Calculated Burn Duration. The burn duration of 75 seconds rests on a specific impulse of 290 seconds and a loss allowance of 300 metres per second, both of which the article assumes.
\[t_b \;=\; \frac{586.2\ \text{kg}}{7.821\ \text{kg/s}} \;=\; 75\ \text{s} \tag{46}\]Equation 47, Oxidiser and Fuel Masses From the Mixture Ratio. The mixture ratio splits the propellant mass into its oxidiser and fuel parts.
\[m_o \;=\; m_p \, \frac{r_m}{1 + r_m}, \qquad m_u \;=\; \frac{m_p}{1 + r_m} \tag{47}\]Equation 48, Propellant Volume. The propellant volume is the sum of the oxidiser and fuel masses over their densities.
\[V_p \;=\; \frac{m_o}{\rho_o} + \frac{m_u}{\rho_u} \tag{48}\]Equation 49, Bespoke Booster Diameter From the Propellant Volume. The article recovers the unpublished diameter by assuming cylindrical tanks at the full body diameter that occupy seventy percent of the booster length. Directory of U.S. Military Rockets and Missiles
\[d \;=\; 2 \sqrt{ \frac{V_p}{\pi \, l_t} } \tag{49}\]Equation 50, Fineness Ratio and Frontal Area. The fineness ratio is the booster length over its diameter and the frontal area is that of a circle of the diameter.
\[f_r = \frac{l_b}{d}, \qquad A_f = \frac{\pi d^2}{4} \tag{50}\]Equation 51, Bespoke Bulk Density of the Loaded Propellant. At the oxidiser to fuel mixture ratio of 2.3 that the article assumes, the loaded propellant has a bulk density of 1,015.3 kilograms per cubic metre.
\[\rho_b \;=\; \frac{m_p}{V_p} \;=\; 1,015.3\ \text{kg}\,\text{m}^{-3} \tag{51}\]Equation 52, Ratio of Span to Diameter. The span over the recovered diameter is a check of the recovered geometry against an ordinary slender configuration.
\[\frac{b}{d} \tag{52}\]Equation 53, Equation of Motion Along the Flight Path. Along the flight path the mass times the acceleration is the thrust less the drag and the component of weight.
\[m \frac{dV}{dt} \;=\; F - D - m g \sin\theta \tag{53}\]Equation 54, Equation of Motion Across the Flight Path. Across the flight path the mass times the speed times the turn rate is the lift less the normal component of weight.
\[m V \frac{d\theta}{dt} \;=\; L - m g \cos\theta \tag{54}\]Equation 55, Lift and Drag. Lift and drag are the dynamic pressure times the reference area times their coefficients.
\[L = \tfrac{1}{2} \rho V^2 S C_l, \qquad D = \tfrac{1}{2} \rho V^2 S C_d \tag{55}\]Equation 56, Ballistic Coefficient. The ballistic coefficient is the mass over the drag coefficient times the reference area.
\[\beta_b = \frac{m}{C_d S} \tag{56}\]Equation 57, Altitude Rate and Mass Flow. The altitude rises at the speed times the sine of the flight path angle while the mass falls at the propellant flow rate.
\[\frac{dz}{dt} \;=\; V \sin\theta, \qquad \frac{dm}{dt} \;=\; -\, \dot{m} \tag{57}\]Equation 58, Bespoke Linear Pitch Programme. The article commands the flight path angle to run linearly from the release angle to the burnout angle over the burn.
\[\theta_c(t) \;=\; \theta_0 + \left( \theta_b - \theta_0 \right) \min\!\left( 1, \; \frac{t}{t_b} \right) \tag{58}\]Equation 59, Bespoke Interpolated Drag Coefficient. The article interpolates the drag coefficient linearly between anchor points it chooses to reproduce the shape every slender supersonic body shares.
\[C_d(M) \;=\; C_d(M_i) + \left[ C_d(M_i') - C_d(M_i) \right] \frac{M - M_i}{M_i' - M_i}, \qquad M_i \le M \le M_i' \tag{59}\]Equation 60, Lift Required by the Commanded Turn. Rearranging the normal equation gives the lift that the commanded pitch programme requires at each instant.
\[L \;=\; m V \frac{d\theta}{dt} + m g \cos\theta \tag{60}\]Equation 61, Structural Coefficient and Payload Fraction. A stage is judged by its structural coefficient, the inert share of inert plus propellant mass, and by its payload fraction. Pegasus rocket
\[\sigma_s \;=\; \frac{m_s}{m_s + m_p}, \qquad f_l \;=\; \frac{m_l}{m_0} \tag{61}\]Equation 62, Bespoke Atmospheric Mass Above the Release Altitude. The air column above an altitude has a mass per area equal to its pressure over gravity, so a release at the twelve kilometres the article takes is above 80.9 percent of the atmosphere’s mass.
\[\frac{m}{S} \bigg|_{\text{above } z} \;=\; \frac{p(z)}{g_0}, \qquad 1 - \frac{p(z)}{p_b(0)} \;=\; 80.9\ \text{percent} \tag{62}\]Equation 63, Bespoke Cost per Second of Test Condition. The article’s figure of merit divides the total cost obligated by the number of flights times the dwell at condition.
\[c_s \;=\; \frac{C_t}{N_f \, \tau} \tag{63}\]Equation 64, Bespoke Cost per Second With No Flights. With the obligated 30,921,064.62 dollars and no flights flown, the article’s figure of merit is undefined.
\[c_s \;=\; \frac{30,921,064.62}{N_f \, \tau} \quad \text{with} \quad N_f = 0 \tag{64}\]Equation 65, Bespoke Dwell at Condition. The dwell is the time within the burn that the Mach number spends above a threshold the article sets for being at condition.
\[\tau \;=\; \int_{0}^{t_b} dt \;\; \text{over the interval where} \;\; M(t) \ge M_d \tag{65}\]Equation 66, Bespoke Split of Cost per Flight. The article separates the cost per flight into a development share that falls with the flight count and a marginal cost that does not.
\[\frac{C_t}{N_f} \;=\; \frac{C_t}{N_f} \bigg|_{\text{development}} + \; c_m \tag{66}\]Equation 67, Bespoke Dwell Fraction of the Integrated Burn. On the article’s integrated ascent with the Mach 6 propellant load the vehicle spends 12.2 seconds above Mach 5, 13.9 percent of the burn.
\[\frac{\tau}{t_b} \;=\; \frac{12.2}{87.8} \;=\; 13.9\ \text{percent} \tag{67}\]Equation 68, Steady Flight Along the Path. At constant speed the thrust balances the drag plus the component of weight along the flight path.
\[F \;=\; D + W \sin\theta \tag{68}\]Equation 69, Flight Path Angle for a Steady State. The steady flight path angle has a sine equal to the excess of thrust over drag divided by the weight.
\[\sin\theta \;=\; \frac{F - D}{W} \tag{69}\]Equation 70, Condition for No Steady State. When the thrust exceeds the drag plus the whole weight, the required sine exceeds one and no steady state exists.
\[F \;>\; D + W \quad \Longrightarrow \quad \sin\theta > 1 \quad \Longrightarrow \quad \text{no steady state exists} \tag{70}\]Equation 71, Throttle Setting to Hold Speed. The throttle setting that holds speed is the drag over the rated thrust.
\[\phi \;=\; \frac{D}{F} \bigg|_{\text{rated}} \tag{71}\]Equation 72, Injector Pressure Drop. The pressure drop across a fixed injector orifice follows the square of the flow, and so the square of the throttle setting. Sutton and Biblarz Huzel and Huang
\[\Delta p_j \;=\; \frac{1}{2 \rho_b} \left( \frac{\dot{m}}{C_j A_j} \right)^2 \;\propto\; \dot{m}^2 \;\propto\; \phi^2 \tag{72}\]Equation 73, Bespoke Range of Dynamic Pressure Across Pitch Programmes. Across the 53 pitch programmes the article integrates, the dynamic pressure at first reaching Mach 5 spans a factor of 72.8.
\[\frac{q_{\max}}{q_{\min}} \bigg|_{M \ge 5} \;=\; 72.8 \tag{73}\]Equation 74, Statutory Thrust Exceeds Lift Test. The statute defines a suborbital rocket in part by thrust exceeding lift for the majority of the powered ascent. 51 U.S.C. 50902
\[F \;>\; L \qquad \text{for the majority of } \; 0 \le t \le t_b \tag{74}\]Equation 75, Load Factor Form of the Statutory Test. Thrust exceeds lift whenever the aerodynamic load factor is below the thrust-to-weight ratio, 1.668 at release.
\[n \;=\; \frac{L}{W}, \qquad F > L \quad \Longleftrightarrow \quad n < \frac{F}{W} \;=\; 1.668 \tag{75}\]Equation 76, Specific Energy and Angular Momentum at Burnout. The burnout speed, radius and flight path angle give the specific orbital energy and specific angular momentum of the coasting ellipse.
\[\varepsilon \;=\; \frac{V^2}{2} - \frac{\mu_E}{r_b}, \qquad \ell \;=\; r_b V \cos\theta \tag{76}\]Equation 77, Semi-Major Axis, Eccentricity and Perigee of the Coasting Ellipse. The energy and angular momentum fix the semi-major axis and eccentricity of the coasting ellipse and hence its perigee radius.
\[a_s \;=\; -\, \frac{\mu_E}{2 \varepsilon}, \qquad e_c \;=\; \sqrt{ 1 + \frac{2 \varepsilon \ell^2}{\mu_E^2} }, \qquad r_p \;=\; a_s \left( 1 - e_c \right) \tag{77}\]Equation 78, Vacuum Instantaneous Impact Point Test. The vacuum instantaneous impact point stays on the Earth when the perigee radius of the coasting ellipse is below the Earth’s radius. 51 U.S.C. 50902
\[r_p \;<\; R_m \quad \Longleftrightarrow \quad \text{the vacuum instantaneous impact point does not leave the surface} \tag{78}\]Equation 79, Bespoke Burnout Speed Against Circular Orbital Speed. The burnout speed of the article’s integrated ascent is 22.9 percent of the circular orbital speed at the burnout radius.
\[V_c \;=\; \sqrt{\frac{\mu_E}{r_b}}, \qquad \frac{V}{V_c} \;=\; 22.9\ \text{percent} \tag{79}\]Notation
- $\dot{m}_a$, the mass flow of air an inlet captures
- $A_c$, the inlet capture area of an air-breathing test article
- $\mathit{Re}_x$, the Reynolds number based on distance from the leading edge
- $x_t$, the distance from the leading edge at which the boundary layer goes turbulent
- $T_w$, the wall temperature of the test article
- $T_r$, the adiabatic wall recovery temperature
- $\gamma$, the ratio of specific heats of air
- $R_e$, the effective radius of the Earth used by the standard atmosphere
- $h_b$, the geopotential altitude of the base of an atmospheric layer
- $T_b$, the temperature at the base of an atmospheric layer
- $p_b$, the pressure at the base of an atmospheric layer
- $\lambda$, the temperature lapse rate of an atmospheric layer
- $g_0$, standard gravity, the constant that defines specific impulse
- $H$, the pressure scale height of the atmosphere
- $\Delta q$, a change in dynamic pressure
- $\Delta z$, the altitude gained between release and the corridor
- $T_0$, the stagnation temperature
- $h_0$, the stagnation enthalpy per unit mass
- $p_0$, the stagnation pressure
- $r_f$, the recovery factor, the fraction of the stagnation temperature rise a wall actually sees
- $\mathit{Pr}$, the Prandtl number of air
- $S_u$, the Sutherland constant for air, with $C_1$ the Sutherland coefficient
- $L_r$, a reference length
- $\dot{Q}$, the stagnation-point convective heat flux
- $k_s$, the Sutton-Graves constant for air
- $R_n$, the nose radius of the test article
- $v_j$, the nozzle exit velocity of the jet
- $p_e$, the nozzle exit pressure, with $p_a$ the ambient pressure at the exit plane
- $A_e$, the nozzle exit area
- $A_t$, the nozzle throat area
- $v_e$, the effective exhaust velocity
- $I_s$, the specific impulse
- $c_*$, the characteristic velocity of the propellant combination
- $C_F$, the nozzle thrust coefficient
- $p_c$, the chamber pressure
- $\epsilon$, the nozzle area ratio
- $M_x$, the Mach number at the nozzle exit plane
- $\Gamma$, the Vandenkerckhove function of the ratio of specific heats
- $T_c$, the combustion chamber temperature
- $F_v$, the vacuum thrust of the engine
- $V_0$, the release velocity, the true airspeed at separation from the carrier
- $\Delta V_k$, the kinematic velocity increment
- $\Delta V_g$, the velocity lost to gravity during powered ascent
- $\Delta V_d$, the velocity lost to drag during powered ascent
- $m_0$, the vehicle mass at engine ignition, with $m_f$ the mass at burnout
- $m_p$, the usable propellant mass
- $m_s$, the structural and inert mass of the vehicle
- $m_l$, the payload mass
- $\zeta$, the propellant mass fraction
- $t_b$, the powered burn duration
- $r_m$, the oxidiser to fuel mixture ratio by mass
- $m_o$, the oxidiser mass, with $m_u$ the fuel mass
- $\rho_o$, the density of liquid oxygen at its normal boiling point, with $\rho_u$ that of the kerosene fuel
- $V_p$, the total propellant volume
- $l_t$, the length of the propellant tankage
- $f_r$, the fineness ratio of the booster, with $l_b$ the booster length
- $A_f$, the frontal area of the booster
- $\rho_b$, the bulk density of the loaded propellant
- $\theta$, the flight path angle above the horizontal
- $C_l$, the lift coefficient, with $C_d$ the drag coefficient
- $\beta_b$, the ballistic coefficient
- $\theta_c$, the flight path angle the pitch programme commands, with $\theta_0$ the release angle and $\theta_b$ the commanded burnout angle
- $M_i$, the Mach number at an anchor point of the drag model
- $\sigma_s$, the structural coefficient, the inert mass as a share of inert plus propellant
- $f_l$, the payload mass fraction
- $c_s$, the cost per second of test condition delivered
- $C_t$, the total cost obligated against the programme
- $N_f$, the number of flights flown
- $\tau$, the time a payload spends inside the test corridor on one flight
- $M_d$, the Mach number above which a flight counts as being at condition
- $c_m$, the marginal cost of one further flight
- $\phi$, the throttle setting, as a fraction of rated thrust
- $\Delta p_j$, the pressure drop across the injector
- $C_j$, the discharge coefficient of an injector orifice, with $A_j$ the total orifice area
- $\varepsilon$, the specific orbital energy of the burnout state
- $\mu_E$, the gravitational parameter of the Earth
- $r_b$, the geocentric radius at burnout
- $a_s$, the semi-major axis of the coasting ellipse
- $e_c$, the eccentricity of the coasting ellipse
- $r_p$, the perigee radius of the coasting ellipse
- $R_m$, the volumetric mean radius of the Earth
- $V_c$, the circular orbital speed at the burnout radius
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Referenced by
- X-Planes: Synthesis and What the Designation Became 2025-12-16
- X-Planes: Bell Textron X-76 SPRINT 2025-12-15
- X-Planes: X-69 through X-75, the Leapfrogged Block 2025-12-14
- X-Planes: General Atomics X-68 LongShot 2025-12-13
- X-Planes: X-67, the Slot Taken by XQ-67A 2025-12-12
- X-Planes: Boeing X-66 2025-12-11
- X-Planes: Aurora Flight Sciences X-65 CRANE 2025-12-10
- X-Planes: Invocon X-64 2025-12-09
- X-Planes: ABL Space Systems X-63 2025-12-08
- X-Planes: Lockheed Martin X-62 VISTA 2025-12-07
- X-Planes: Dynetics X-61 Gremlins 2025-12-06