Analysis of generic scramjet external nozzle flowfields employing simulant gases

Tatum, Kenneth E.; Monta, W. J.; Witte, David W.; Walters, Robert W.

doi:10.2514/6.1990-5242

Cited by 10 publications

(3 citation statements)

References 3 publications

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“…30 During the National Aero-Space Plane (NASP) program, significant work was done to investigate the use of cold-gas mixtures to simulate powered scramjet exhaust products in ground test facilities. [31][32][33] This technique was investigated in the supersonic and hypersonic speed regimes (Mach 4-10) with powered metric aftbody models to develop the technique and measure external nozzle pressures, exhaust plume impingement on wing surfaces and aftbody forces and moments. Analysis to examine the correlation of cold simulant gases to hot combustion products was initiated, but not completed due to the termination of this program.The X-43A flight project undertook a significant ground testing and computational effort to build the pre-flight vehicle database.…”

Section: Aero-propulsive Interactionsmentioning

confidence: 99%

Aerosciences, Aero-Propulsion and Flight Mechanics Technology Development for NASA's Next Generation Launch Technology Program

Cockrell

2003

12th AIAA International Space Planes and Hypersonic Systems and Technologies

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The Next Generation Launch Technology (NGLT) program, Vehicle Systems Research and Technology (VSR&T) project is pursuing technology advancements in aerothermodynamics, aeropropulsion and flight mechanics to enable development of future reusable launch vehicle (RLV) systems. The current design trade space includes rocket-propelled, hypersonic airbreathing and hybrid systems in two-stage and single-stage configurations. Aerothermodynamics technologies include experimental and computational databases to evaluate stage separation of two-stage vehicles as well as computational and trajectory simulation tools for this problem. Additionally, advancements in high-fidelity computational tools and measurement techniques are being pursued along with the study of flow physics phenomena, such as boundary-layer transition. Aero-propulsion technology development includes scramjet flowpath development and integration, with a current emphasis on hypervelocity (Mach 10 and above) operation, as well as the study of aero-propulsive interactions and the impact on overall vehicle performance. Flight mechanics technology development is focused on advanced guidance, navigation and control (GN&C) algorithms and adaptive flight control systems for both rocketpropelled and airbreathing vehicles.

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Section: Aero-propulsive Interactionsmentioning

confidence: 99%

Aerosciences, Aero-Propulsion and Flight Mechanics Technology Development for NASA's Next Generation Launch Technology Program

Cockrell

2003

12th AIAA International Space Planes and Hypersonic Systems and Technologies

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“…Predictions for surface pressure, flow-field quantities and integrated forces and moments have compared well to available experimental data at unpowered and simulated powered conditions in previous studies. [9][10][11][12][13] Another CFD tool used in the Hyper-X scramjet flowpath design and analysis is the Viscous Upwind Algorithm for Complex Flow Analysis (VULCAN). 14 Two additional tools are used for analysis of the internal propulsion flowpath.…”

Section: Analysis Toolsmentioning

confidence: 99%

Integrated aero-propulsive CFD methodology for the Hyper-X flight experiment

Cockrell

Walter

Robert³

et al. 2000

18th Applied Aerodynamics Conference

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Computational fluid dynamics (CFD) tools have been used extensively in the analysis and development of the X-43A Hyper-X Research Vehicle (HXRV). A significant element of this analysis is the prediction of integrated vehicle aero-propulsive performance, which includes an integration of aerodynamic and propulsion flow fields. This paper describes analysis tools used and the methodology for obtaining pre-flight predictions of longitudinal performance increments. The use of higher-fidelity methods to examine flow-field characteristics and scramjet flowpath component performance is also discussed. Limited comparisons with available ground test data are shown to illustrate the approach used to calibrate methods and assess solution accuracy. Inviscid calculations to evaluate lateral-directional stability characteristics are discussed. The methodology behind 3D tip-to-tail calculations is described and the impact of 3D exhaust plume expansion in the aftbody region is illustrated. Finally, future technology development needs in the area of hypersonic propulsion-airframe integration analysis are discussed.

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“…Before any CFD code can be used as an analysis tool, code calibration is essential for the types of flows of interest to provide a level of confidence in the ability of the code to accurately predict the fluid dynamics of the problem. Previous studies using GASP have shown that it has the ability to accurately predict complex three-dimensional hypersonic flows past configurations representative of NASP forebodies [3][4][5] , as well as the two-dimensional powered effects on model aftbodies 6,7 . In the current study, code calibration will be made using a three-dimensional powered aftbody model.…”

Section: Code Calibration Studymentioning

confidence: 99%

CFD code calibration and inlet-fairing effects on a 3D hypersonic powered-simulation model

Lawrence

Kenneth²

1993

23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference

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A three-dimensional (3D) computational study has been performed addressing issues related to the wind tunnel testing of a hypersonic powered-simulation model. The study consisted of three objectives. The first objective was to calibrate a state-of-the-art computational fluid dynamics (CFD) code in its ability to predict hypersonic powered-simulation flows by comparing CFD solutions with experimental surface pressure data. Aftbody lower surface pressures were well predicted, but lower surface wing pressures were less accurately predicted. The second objective was to determine the 3D effects on the aftbody created by fairing over the inlet; this was accomplished by comparing the CFD solutions of two closed-inlet powered configurations with a flowing-inlet powered configuration. Although results at four freestream Mach numbers indicate that the exhaust plume tends to isolate the aftbody surface from most forebody flowfield differences, a smooth inlet fairing provides the least aftbody force and moment variation compared to a flowing inlet. The final objective was to predict and understand the 3D characteristics of exhaust plume development at selected points on a representative flight path. Results showed a dramatic effect of plume expansion onto the wings as the freestream Mach number and corresponding nozzle pressure ratio are increased. NomenclatureM Mach number NPR nozzle pressure ratio, p t,jet / p pressure, Pa Re Reynolds number, 1/m T temperature, K X aftbody aftbody length from cowl trailing edge to body trailing edge x, y, z streamwise, spanwise, and vertical coordinates Y aftbody model fuselage maximum semispan α angle of attack, degrees ρ density, kg/m 3 Subscripts freestream conditions throat conditions at the internal nozzle throat t, jet jet total conditions wall conditions at a solid wall boundary p ∞ ∞

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Analysis of generic scramjet external nozzle flowfields employing simulant gases

Cited by 10 publications

References 3 publications

Aerosciences, Aero-Propulsion and Flight Mechanics Technology Development for NASA's Next Generation Launch Technology Program

Aerosciences, Aero-Propulsion and Flight Mechanics Technology Development for NASA's Next Generation Launch Technology Program

Integrated aero-propulsive CFD methodology for the Hyper-X flight experiment

CFD code calibration and inlet-fairing effects on a 3D hypersonic powered-simulation model

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