Hypersonic parabolized Navier-Stokes code validation on a sharp nosecone

Huebner, Lawrence D.; Pittman, James L.; Dilley, Arthur D.

doi:10.2514/3.45816

Cited by 6 publications

(5 citation statements)

References 9 publications

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“…The method is a cell-centered finite volume scheme that uses upwind/relaxation methods and has been validated by numerous comparisons with data. In one of the validation studies, the PNS mode was evaluated by Huebner et al 18 by comparison with data at MO, = 7.95. By considering only axisymmetric bodies and primarily using space-marching techniques, the analysis was performed economically, allowing a thorough investigation of the aerodynamic performance of minimum-drag body shapes.…”

Section: Computational Approach and Methodologymentioning

confidence: 99%

Minimum-drag axisymmetric bodies in the supersonic/hypersonic flow regimes

Mason

Lee

1994

Journal of Spacecraft and Rockets

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A study of minimum-drag body shapes was conducted over a Mach range from 3 to 12. Numerical results show that power-law bodies result in low-drag shapes, where the power n = 0.69 (l/d = 3) or n = 0.70 (l/d = 5) shapes have lower drag than theoretical minimum results (« = 0.75 or 0.66, depending on the particular form of the theory). To evaluate the results, a numerical analysis was made, including viscous effects and the effect of a gas model. None of these considerations altered the conclusions. The Hayes minimum-drag body was analyzed and had a higher drag than the optimum power-law body. d i n r T r re f x, y, 0 Nomenclature = drag coefficient based on the maximum cross-sectional area = skin-friction coefficient = pressure coefficient = body diameter at the base = marching plane index = unified supersonic-hypersonic similarity parameter, = body length = freestream Mach number = power-law exponent = body radius = temperature at the body surface = freestream temperature z -physical coordinates = circumferential angle

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Section: Computational Approach and Methodologymentioning

confidence: 99%

Minimum-drag axisymmetric bodies in the supersonic/hypersonic flow regimes

Mason

Lee

1994

Journal of Spacecraft and Rockets

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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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“…Prior research indicates that y + values less than will yield an adequate solution 3 . Both the Euler and PNS solutions were initialized using the experimental pressure data at the entrance plane boundary.…”

Section: D Proceduresmentioning

confidence: 99%

“…The flow-field features represented here are typical of those seen in designs for scramjet engines. It is appropriate to investigate the forebody/inlet region of the engine separately because the flow is independent of the nozzle and aftbody regions 3 . Experimental data, obtained previously from a wind tunnel test of this model, were used to assess the accuracy of CFD solutions and to compute the internal drag force.…”

Section: Model Descriptionmentioning

confidence: 99%

“…The forebody surface of the vehicle provides compression of the flow before reaching the inlet, and the aftbody surface serves as an extension of the nozzle to expand the flow and provide for maximum thrust 2 . Additionally, the engine modules are mounted inside the vehicle's bow shock wave, which provides for a significant size and weight savings for the propulsion system 3 . The boundary layer that forms on the forebody surface is swallowed by the inlet.…”

Section: Introductionmentioning

confidence: 99%

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Generic hypersonic inlet module analysis

Cockrell

Lawrence

1991

9th Applied Aerodynamics Conference

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A computational study associated with an internal inlet drag analysis was performed for a generic hypersonic inlet module. The purpose of this study was to determine the feasibility of computing the internal drag force for a generic scramjet engine module using computational methods. The computational study consisted of obtaining two-dimensional (2D) and threedimensional (3D) computational fluid dynamics (CFD) solutions using the Euler and parabolized Navier-Stokes (PNS) equations. The solution accuracy was assessed by comparisons with experimental pitot pressure data. The CFD analysis indicates that the 3D PNS solutions show the best agreement with experimental pitot pressure data. The internal inlet drag analysis consisted of obtaining drag force predictions based on experimental data and 3D CFD solutions. A comparative assessment of each of the drag prediction methods is made and the sensitivity of CFD drag values to computational procedures is documented. The analysis indicates that the CFD drag predictions are highly sensitive to the computational procedure used.

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Hypersonic parabolized Navier-Stokes code validation on a sharp nosecone

Cited by 6 publications

References 9 publications

Minimum-drag axisymmetric bodies in the supersonic/hypersonic flow regimes

Minimum-drag axisymmetric bodies in the supersonic/hypersonic flow regimes

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

Generic hypersonic inlet module analysis

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