The NASA Langley Scramjet Test Complex

Guy, R. W.; Rogers, R. C.; Puster, Richard L.; Rock, Kenneth E.; Diskin, G L

doi:10.2514/6.1996-3243

Cited by 64 publications

(19 citation statements)

References 28 publications

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“…Figure 1 has been thoroughly characterized in NASA's Arc-Heated Scramjet Test Facility (AHSTF). 5 This test facility is commonly operated in free jet mode, but it has been modified to support direct-connect testing of this hydrocarbon-fueled flowpath. Test conditions covering the range of interest to the HF2 experiment (M ∞ = 6 -8) are achievable in AHSTF using three facility nozzles (nozzle exit Mach 2.51, 3.00, and 3.46).…”

Section: IImentioning

confidence: 99%

Combustor Operability and Performance Verification for HIFiRE Flight 2

Storch

Bynum

Liu

et al. 2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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As part of the Hypersonic International Flight Research Experimentation (HIFiRE)Direct-Connect Rig (HDCR) test and analysis activity, three-dimensional computational fluid dynamics (CFD) simulations were performed using two Reynolds-Averaged Navier Stokes solvers. Measurements obtained from ground testing in the NASA Langley ArcHeated Scramjet Test Facility (AHSTF) were used to specify inflow conditions for the simulations and combustor data from four representative tests were used as benchmarks. Test cases at simulated flight enthalpies of Mach 5.84, 6.5, 7.5, and 8.0 were analyzed. Modeling parameters (e.g., turbulent Schmidt number and compressibility treatment) were tuned such that the CFD results closely matched the experimental results. The tuned modeling parameters were used to establish a standard practice in HIFiRE combustor analysis. Combustor performance and operating mode were examined and were found to meet or exceed the objectives of the HIFiRE Flight 2 experiment. In addition, the calibrated CFD tools were then applied to make predictions of combustor operation and performance for the flight configuration and to aid in understanding the impacts of ground and flight uncertainties on combustor operation. Nomenclature

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Section: IImentioning

confidence: 99%

Combustor Operability and Performance Verification for HIFiRE Flight 2

Storch

Bynum

Liu

et al. 2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…For this reason, significant scramjet research has been conducted in many parts of the world 1 . Ground testing in continuous flow facilities has comprised most of the scramjet testing below Mach 8 2 , whereas shock tunnels with flow durations of the order of 1-10 ms have been used for testing above Mach 7. The Centre for Hypersonics at the University of Queensland has routinely performed scramjet testing in shock tunnels for many years 3 .…”

Section: Introductionmentioning

confidence: 99%

Flight Data Analysis of the HYSHOT 2

Hass

Smart

Paull

2005

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference

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The development of scramjet propulsion for alternative launch and payload delivery capabilities has comprised largely of ground experiments for the last 40 years. With the goal of validating the use of short duration ground test facilities, the University of Queensland, supported by a large international contingency, devised a ballistic re-entry vehicle experiment called HyShot to achieve supersonic combustion in flight above Mach 7.5. It consisted of a double wedge intake and two back-to-back constant area combustors; one supplied with hydrogen fuel at an equivalence ratio of 0.33 and the other un-fueled.

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“…Note that Eqs. (10)(11)(12)(13)(14)(15) are the same as those applied to cases with a uniform line of sight; only the formulation of the absorbance in Eq. (9) is affected by nonuniformities in the beam path.…”

Section: Simulation Of Path-integrated Wms Linementioning

confidence: 99%

“…H 2 -air combustion is used to heat the flow before expansion through a supersonic nozzle [14,15]. During testing of the TDLAS mass-flux sensor, a Mach 2.65 nozzle was used to simulate Mach 6 and 7 flight enthalpies, producing the nominal test conditions summarized in Table 1.…”

Section: Measurements In Nasa Langley Dcsctfmentioning

confidence: 99%

Supersonic Mass-Flux Measurements via Tunable Diode Laser Absorption and Nonuniform Flow Modeling

Chang¹,

Strand²,

Jeffries³

et al. 2011

AIAA Journal

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Measurements of mass flux are obtained in a vitiated supersonic ground-test facility using a sensor based on lineof-sight diode laser absorption of water vapor. Mass flux is determined from the product of measured velocity and density. The relative Doppler shift of an absorption transition for beams directed upstream and downstream in the flow is used to measure velocity. Temperature is determined from the ratio of absorption signals of two transitions ( 1 1349 nm and 2 1341:5 nm) and is coupled with a facility pressure measurement to obtain density. The sensor exploits wavelength-modulation spectroscopy with second-harmonic detection for large signal-to-noise ratios and normalization with the 1f signal for rejection of non-absorption-related transmission fluctuations. The sensor line of sight is translated both vertically and horizontally across the test section for spatially resolved measurements. Time-resolved measurements of mass flux are used to assess the stability of flow conditions produced by the facility. Measurements of mass flux are within 1.5% of the value obtained using a facility predictive code. The distortion of the wavelength-modulation spectroscopy lineshape caused by boundary layers along the laser line of sight is examined and the subsequent effect on the measured velocity is discussed. A method for correcting measured velocities for flow nonuniformities is introduced and application of this correction brings measured velocities within 4 m=s of the predicted value in a 1630 m=s flow.

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The NASA Langley Scramjet Test Complex

Cited by 64 publications

References 28 publications

Combustor Operability and Performance Verification for HIFiRE Flight 2

Combustor Operability and Performance Verification for HIFiRE Flight 2

Flight Data Analysis of the HYSHOT 2

Supersonic Mass-Flux Measurements via Tunable Diode Laser Absorption and Nonuniform Flow Modeling

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