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Revisiting Turbulence Model Validation for High-Mach Number Axisymmetric Compression Corner FlowsTwo axisymmetric shock-wave/boundary-layer interaction (SWBLI) cases are used to benchmark one- and two-equation Reynolds-averaged Navier-Stokes (RANS) turbulence models. This validation exercise was executed in the philosophy of the NASA Turbulence Modeling Resource and the AIAA Turbulence Model Benchmarking Working Group. Both SWBLI cases are from the experiments of Kussoy and Horstman for axisymmetric compression corner geometries with SWBLI inducing flares of 20 and 30 degrees, respectively. The freestream Mach number was approximately 7. The RANS closures examined are the Spalart-Allmaras one-equation model and the Menter family of kappa − omega two equation models including the Baseline and Shear Stress Transport formulations. The Wind-US and CFL3D RANS solvers are employed to simulate the SWBLI cases. Comparisons of RANS solutions to experimental data are made for a boundary layer survey plane just upstream of the SWBLI region. In the SWBLI region, comparisons of surface pressure and heat transfer are made. The effects of inflow modeling strategy, grid resolution, grid orthogonality, turbulent Prandtl number, and code-to-code variations are also addressed.
Document ID
20150002106
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Georgiadis, Nicholas J. (NASA Glenn Research Center Cleveland, OH United States)
Rumsey, Christopher L. (NASA Langley Research Center Hampton, VA United States)
Huang, George P. (Wright State Univ. Dayton, OH, United States)
Date Acquired
February 25, 2015
Publication Date
January 5, 2015
Subject Category
Aerodynamics
Report/Patent Number
GRC-E-DAA-TN19563
Meeting Information
Meeting: AIAA SciTech Conference
Location: Kissimmee, FL
Country: United States
Start Date: January 5, 2015
End Date: January 9, 2015
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 794072.02.03.02.01
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Shock Wave
Validation
Turbulence

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