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Wind-US Code Physical Modeling Improvements to Complement Hypersonic Testing and EvaluationThis report gives an overview of physical modeling enhancements to the Wind-US flow solver which were made to improve the capabilities for simulation of hypersonic flows and the reliability of computations to complement hypersonic testing. The improvements include advanced turbulence models, a bypass transition model, a conjugate (or closely coupled to vehicle structure) conduction-convection heat transfer capability, and an upgraded high-speed combustion solver. A Mach 5 shock-wave boundary layer interaction problem is used to investigate the benefits of k- s and k-w based explicit algebraic stress turbulence models relative to linear two-equation models. The bypass transition model is validated using data from experiments for incompressible boundary layers and a Mach 7.9 cone flow. The conjugate heat transfer method is validated for a test case involving reacting H2-O2 rocket exhaust over cooled calorimeter panels. A dual-mode scramjet configuration is investigated using both a simplified 1-step kinetics mechanism and an 8-step mechanism. Additionally, variations in the turbulent Prandtl and Schmidt numbers are considered for this scramjet configuration.
Document ID
20090027874
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Georgiadis, Nicholas J. (NASA Glenn Research Center Cleveland, OH, United States)
Yoder, Dennis A. (NASA Glenn Research Center Cleveland, OH, United States)
Towne, Charles S. (NASA Glenn Research Center Cleveland, OH, United States)
Engblom, William A. (Embry-Riddle Aeronautical Univ. Daytona Beach, FL, United States)
Bhagwandin, Vishal A. (Embry-Riddle Aeronautical Univ. Daytona Beach, FL, United States)
Power, Greg D. (Arnold Engineering Development Center Arnold AFS, TN, United States)
Lankford, Dennis W. (Arnold Engineering Development Center Arnold AFS, TN, United States)
Nelson, Christopher C. (Innovative Technology Applications Co. Chesterfield, MO, United States)
Date Acquired
August 24, 2013
Publication Date
July 1, 2009
Subject Category
Aeronautics (General)
Report/Patent Number
NASA/TM-2009-215615
E-16931
AIAA-2009-193
Meeting Information
Meeting: 47th Aerospace Sciences Meeting
Location: Orlando, Fl
Country: United States
Start Date: January 5, 2009
End Date: January 8, 2009
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 5999489.02.07.03.03.02.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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