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Two-equation turbulence modeling for 3-D hypersonic flowsAn investigation to verify, incorporate and develop two-equation turbulence models for three-dimensional high speed flows is presented. The current design effort of hypersonic vehicles has led to an intensive study of turbulence models for compressible hypersonic flows. This research complements an extensive review of experimental data and the current development of 2D turbulence models. The review of experimental data on 2D and 3D flows includes complex hypersonic flows with pressure profiles, skin friction, wall heat transfer, and turbulence statistics data. In a parallel effort, turbulence models for high speed flows have been tested against flat plate boundary layers, and are being tested against the 2D database. In the present paper, we present the results of 3D Navier-Stokes numerical simulations with an improved k-omega two-equation turbulence model against experimental data and empirical correlations of an adiabatic flat plate boundary layer, a cold wall flat plate boundary layer, and a 3D database flow, the interaction of an oblique shock wave and a thick turbulent boundary layer with a free stream Mach number = 8.18 and Reynolds number = 5 x 10 to the 6th.
Document ID
19930038337
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bardina, J. E.
(MCAT Inst. San Jose, CA, United States)
Coakley, T. J.
(NASA Ames Research Center Moffett Field, CA, United States)
Marvin, J. G.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
December 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-5064
Meeting Information
Meeting: AIAA, International Aerospace Planes Conference
Location: Orlando, FL
Country: United States
Start Date: December 1, 1992
End Date: December 4, 1992
Sponsors: AIAA
Accession Number
93A22334
Funding Number(s)
CONTRACT_GRANT: NCC2-15
Distribution Limits
Public
Copyright
Other

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