Investigation of a hypersonic crossing shock wave/turbulent boundary layer interaction

N. Narayanswami; D. D. Knight; C. C. Horstman

doi:10.1007/BF01414746

Investigation of a hypersonic crossing shock wave/turbulent boundary layer interaction

N. Narayanswami, D. D. Knight, C. C. Horstman

School of Engineering, Mechanical & Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

20 Scopus citations

Abstract

A combined theoretical and experimental study is presented for the interaction between crossing shock waves generated by (10°, 10°) sharp fins and a flat plate turbulent boundary layer at Mach 8.3. The theoretical model is the full 3-D mean compressible Reynolds-averaged Navier-Stokes RANS) equations incorporating the algebraic turbulent eddy viscosity model of Baldwin and Lomax. A grid refinement study indicated that adequate resolution of the flowfield has been achieved. Computed results agree well with experiment for surface pressure and surface flow patterns and for pitot pressure and yaw angle profiles in the flowfield. The computations, however, significantly overpredict surface heat transfer. Analysis of the computed flowfield results indicates the formation of complex streamline and wave structures within the interaction region.

Original language	English (US)
Pages (from-to)	35-48
Number of pages	14
Journal	Shock Waves
Volume	3
Issue number	1
DOIs	https://doi.org/10.1007/BF01414746
State	Published - Mar 1993

All Science Journal Classification (ASJC) codes

Mechanical Engineering
General Physics and Astronomy

Keywords

Crossing shock
Interaction
Turbulent boundary layer

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10.1007/BF01414746

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abstract = "A combined theoretical and experimental study is presented for the interaction between crossing shock waves generated by (10°, 10°) sharp fins and a flat plate turbulent boundary layer at Mach 8.3. The theoretical model is the full 3-D mean compressible Reynolds-averaged Navier-Stokes RANS) equations incorporating the algebraic turbulent eddy viscosity model of Baldwin and Lomax. A grid refinement study indicated that adequate resolution of the flowfield has been achieved. Computed results agree well with experiment for surface pressure and surface flow patterns and for pitot pressure and yaw angle profiles in the flowfield. The computations, however, significantly overpredict surface heat transfer. Analysis of the computed flowfield results indicates the formation of complex streamline and wave structures within the interaction region.",

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AU - Narayanswami, N.

AU - Knight, D. D.

AU - Horstman, C. C.

PY - 1993/3

Y1 - 1993/3

N2 - A combined theoretical and experimental study is presented for the interaction between crossing shock waves generated by (10°, 10°) sharp fins and a flat plate turbulent boundary layer at Mach 8.3. The theoretical model is the full 3-D mean compressible Reynolds-averaged Navier-Stokes RANS) equations incorporating the algebraic turbulent eddy viscosity model of Baldwin and Lomax. A grid refinement study indicated that adequate resolution of the flowfield has been achieved. Computed results agree well with experiment for surface pressure and surface flow patterns and for pitot pressure and yaw angle profiles in the flowfield. The computations, however, significantly overpredict surface heat transfer. Analysis of the computed flowfield results indicates the formation of complex streamline and wave structures within the interaction region.

AB - A combined theoretical and experimental study is presented for the interaction between crossing shock waves generated by (10°, 10°) sharp fins and a flat plate turbulent boundary layer at Mach 8.3. The theoretical model is the full 3-D mean compressible Reynolds-averaged Navier-Stokes RANS) equations incorporating the algebraic turbulent eddy viscosity model of Baldwin and Lomax. A grid refinement study indicated that adequate resolution of the flowfield has been achieved. Computed results agree well with experiment for surface pressure and surface flow patterns and for pitot pressure and yaw angle profiles in the flowfield. The computations, however, significantly overpredict surface heat transfer. Analysis of the computed flowfield results indicates the formation of complex streamline and wave structures within the interaction region.

KW - Crossing shock

KW - Interaction

KW - Turbulent boundary layer

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Investigation of a hypersonic crossing shock wave/turbulent boundary layer interaction

Abstract

All Science Journal Classification (ASJC) codes

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