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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
20080006846
Document Type
Preprint (Draft being sent to journal)
Authors
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)
Gaffney, R. L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 24, 2013
Publication Date
January 1, 2007
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
AIAA Paper 2005-1098
Funding Number(s)
CONTRACT_GRANT: FA9101-04-C-0015
OTHER: 23R-065-50-9177-01
CONTRACT_GRANT: NAG1-03030
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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