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Supersonic boundary-layer flow turbulence modelingBaldwin-Lomax and kappa-epsilon turbulence models were modified for use in Navier-Stokes numerical computations of Mach 2.9 supersonic turbulent boundary layer flows along compression ramps. The computational results of Reynolds shear stress profiles were compared with experimental data. The Baldwin-Lomax model was modified to account for the Reynolds shear stress amplification within the flow field. A hybrid kappa-epsilon model with viscous sublayer turbulence treatment was constructed to predict the Reynolds shear stress profiles within the entire flow field. These modified turbulence models were effective for the computations of the surface pressure and the skin friction factor variations along an 8 deg ramp surface. The hybrid kappa-epsilon model could improve the predictions of the Reynolds shear stress profile and the skin friction factor near the corner of a 16 deg ramp.
Document ID
19930005569
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wang, Chi-Rong
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1993
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-105893
NAS 1.15:105893
E-7360
Meeting Information
Meeting: International Conference on Near-Wall Turbulence Flows
Location: Tempe, AZ
Country: United States
Start Date: March 15, 1993
End Date: March 18, 1993
Accession Number
93N14758
Funding Number(s)
PROJECT: RTOP 505-62-52
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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