Computation of crossing shock/turbulent boundary layer interaction at Mach 8.3

A three-dimensional (3D) hypersonic crossing shock wave/turbulent boundary-layer interaction is examined numerically at Mach 8.3. The test geometry consists of a pair of opposing sharp fins of angle alpha = 15 deg, mounted on a flat plate. Two theoretical models are evaluated. The full (3D) Reynolds...

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Bibliographic Details
Published in:AIAA journal 1993-08, Vol.31 (8), p.1369-1376
Main Authors: Narayanswami, N, Horstman, C. C, Knight, D. D
Format: Article
Language:English
Subjects:
Aerodynamics
Compressible flows
shock and detonation phenomena
Exact sciences and technology
Fluid dynamics
Fundamental areas of phenomenology (including applications)
Physics
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Summary:A three-dimensional (3D) hypersonic crossing shock wave/turbulent boundary-layer interaction is examined numerically at Mach 8.3. The test geometry consists of a pair of opposing sharp fins of angle alpha = 15 deg, mounted on a flat plate. Two theoretical models are evaluated. The full (3D) Reynolds-averaged Navier-Stokes equations are solved using the Baldwin-Lomax and the Rodi (modified k-epsilon) turbulence models. Computed results for both cases show good agreement with experiment for flat plate surface pressure and for flowfield profiles of pitot pressure and yaw angle, indicating that the flowfield is primarily rotational and inviscid. Fair to poor agreement is obtained for surface heat transfer, indicating a need for more accurate turbulence models. The overall flowfield structure is similar to that observed in previous crossing shock interaction studies.
ISSN:0001-1452
1533-385X
DOI:10.2514/3.11784