HIFiRE Direct-Connect Rig (HDCR) Phase I Scramjet Test Results from the NASA Langley Arc-Heated Scramjet Test Facility

Cabell, Karen F.; Hass, Neal E.; Storch, Andrea M.; Gruber, Mark

doi:10.2514/6.2011-2248

Cited by 32 publications

(30 citation statements)

References 10 publications

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“…Table 3 shows the specific test cases identified for detailed analysis. 7,8 The inflow boundary condition for each case consisted of the conditions shown in the facility plenum. The facility nozzle was also modeled in each case.…”

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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“…Although the ground test 125.1 was simulated with Mach 6.5 enthalpy conditions, the facility nozzle is not capable of producing the correct isolator Mach number, and therefore cannot be considered directly comparable to the flight condition. 11 However, it does allow for a comparison of the differences expected between flight and ground tests. For scaling of the surface pressure coefficients, the isolator entrance centerline pressure was used in place of the free-stream pressure.…”

Section: Vic Simulation Resultsmentioning

confidence: 99%

“…This fuel has been tested alongside pure ethylene in the NASA Langley Research Center's AHSTF using the HDCR to determine fueling schedules that provide high pressure rise through the flowpath while also providing acceptable isolator margins that decouple the inlet from the combustor and lower the risk of inlet unstart. 11 A simplified volumetric heat release model is explored for suitability, as its computational requirements are far less than the reduced order combustion model. The region of volumetric heat release presented herein is restricted as shown in Figure 4, however, evaluation of the heat release distribution observed with the TP2 model presented later in this paper will be used to refine the region of heat release for future simulation.…”

Section: Ivb Simulation Parameters and Modelsmentioning

confidence: 99%

“…10 Ground tests of the HIFiRE Direct Connect Rig (HDCR) have been performed at the NASA Langely Arc-Heated Scramjet Test Facility (AHSTF) with an emphasis on fueling schedules at steady state operating conditions that provide an acceptable compromise between high heat release and safe isolator operability margins. 11,12 Simulations of the ground tests, for which experimental data is already available, permits fine tuning of the CFD parameters to ensure that the physics of this complex regime are being captured accurately.…”

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confidence: 99%

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Exploratory Simulations of the HIFiRE 2 Scramjet Flowpath

Yentsch¹,

Gaitonde²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Steady-state Reynolds Averaged Navier-Stokes (RANS) simulations of a hypersonic airbreathing propulsion system have been performed to examine key aero-propulsive phenomena, including the effects of turbulence, heat release, and viscous/inviscid interactions. The simulations are anchored in the HIFiRE-2 flight test and supporting ground tests performed at the NASA Langely Arc Heated Scramjet Test Facility. Through comparison to experimental data from the ground tests, initial simulations focus on formation of grids and calibration of heat release models, including volumetric heat release as well as a reduced-order bi-component ethylene-methane combustion model. For the ground test simulations, unfueled, volumetric heat release, and the reduced order combustion model results are compared to experimental data and each other. Flight test simulations are compared to ground test simulations, and the similarities and differences are evaluated. In doing so, a foundation is prepared for forthcoming time-accurate simulations of in flight mode transition and unstart.

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“…Phase I test results and companion CFD results have recently been reported. 3,4,5 The ground-test engine provides an opportunity for making absorption measurements at the same axial flowpath location as the intended flight instrument. A research-grade TDLAS instrument was recently integrated onto the HDCR for data collection during the Phase II tests.…”

Section: Introductionmentioning

confidence: 99%

Optical Measurements at the Combustor Exit of the HIFiRE 2 Ground Test Engine

Brown

Herring

Cabell

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The development of optical techniques capable of measuring in-stream flow properties of air breathing hypersonic engines is a goal of the Aerospace Propulsion Division at AFRL. Of particular interest are techniques such as tunable diode laser absorption spectroscopy that can be implemented in both ground and flight test efforts. We recently executed a measurement campaign at the exit of the combustor of the HIFiRE 2 ground test engine during Phase II operation of the engine. Data was collected in anticipation of similar data sets to be collected during the flight experiment. The ground test optical data provides a means to evaluate signal processing algorithms particularly those associated with limited line of sight tomography. Equally important, this in-stream data was collected to compliment data acquired with surface-mounted instrumentation and the accompanying flowpath modeling efforts -both CFD and lower order modeling. Here we discuss the specifics of hardware and data collection along with a coarse-grained look at the acquired data and our approach to processing and analyzing it.

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HIFiRE Direct-Connect Rig (HDCR) Phase I Scramjet Test Results from the NASA Langley Arc-Heated Scramjet Test Facility

Abstract: = fuel equivalence ratio injected at secondary injection station  TOT = total equivalence ratio =  P1 +  CI +  S1  B = total fuel equivalence ratio burned x = axial distance from isolator entrance (in) t = time (seconds)

Cited by 32 publications

References 10 publications

Combustor Operability and Performance Verification for HIFiRE Flight 2

Combustor Operability and Performance Verification for HIFiRE Flight 2

Exploratory Simulations of the HIFiRE 2 Scramjet Flowpath

Optical Measurements at the Combustor Exit of the HIFiRE 2 Ground Test Engine

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