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Numerical simulation of crossing/turbulent boundary layer interaction at Mach 8.3 comparison of zero and two-equation turbulence modelsA 3D hypersonic crossing shock wave/turbulent boundary layer interaction is examined numerically. The test geometry consists of a pair of opposing sharp fins of angle alpha = 15 deg mounted on a flat plate. The freestream Mach number is 8.28. Two theoretical models are evaluated. The full 3D Reynolds-averaged Navier-Stokes equations are solved using the Baldwin-Lomax algebraic turbulent eddy viscosity model and the Rodi turbulence model. Computed results for both cases show good agreement with experiment for flat plate surface pressure and for pitot pressure and yaw angle profiles in the flowfield. General agreement is obtained for surface flow direction. 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.
Document ID
19930040864
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Narayanswami, N.
(Rutgers Univ. Piscataway, NJ, United States)
Horstman, C. C.
(NASA Ames Research Center Moffett Field, CA, United States)
Knight, D. D.
(Rutgers Univ. Piscataway, NJ, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0779
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A24861
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-86-0266
Distribution Limits
Public
Copyright
Other

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