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Role of Turbulent Prandtl Number on Heat Flux at Hypersonic Mach NumbersA new turbulence model suited for calculating the turbulent Prandtl number as part of the solution is presented. The model is based on a set of two equations: one governing the variance of the enthalpy and the other governing its dissipation rate. These equations were derived from the exact energy equation and thus take into consideration compressibility and dissipation terms. The model is used to study two cases involving shock wave/boundary layer interaction at Mach 9.22 and Mach 5.0. In general, heat transfer prediction showed great improvement over traditional turbulence models where the turbulent Prandtl number is assumed constant. It is concluded that using a model that calculates the turbulent Prandtl number as part of the solution is the key to bridging the gap between theory and experiment for flows dominated by shock wave/boundary layer interactions.
Document ID
20050123602
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Gaffney, R. L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Xiao, X. (North Carolina State Univ. Raleigh, NC, United States)
Edwards, J. R. (North Carolina State Univ. Raleigh, NC, United States)
Hassan, H. A. (North Carolina State Univ. Raleigh, NC, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2005
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2005-1098
Meeting Information
Meeting: 43rd AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 10, 2005
End Date: January 13, 2005
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAG1-03030
OTHER: 23-065-50-SL
CONTRACT_GRANT: FA9101-04-C-0015
Distribution Limits
Public
Copyright
Public Use Permitted.

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