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Steady and nonsteady supersonic turbulent afterbody flowThe effect of the specific heat ratio gamma of the incoming ideal gas on the flow properties, especially on pressure distributions along the base and sting surfaces and on reattachment distance, was investigated. The specific heat ratios considered were gamma = 1.2, 1.4, and 1.667. Also, effects of other major parameters, such as eddy-viscosity coefficient (or effective Reynolds number) and Mach number, on the afterbody pressure and reattachment distance were studied and are discussed. Evolution of shock induced flow and stabilization time were examined and are discussed for a transient problem. The important influence of the flow-field geometry, pressure distributions, and reattachment distance on the aerodynamics radiative heat transfer for an atmosphere entry probe in high speed flight are briefly described.
Document ID
19810008458
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Yoshikawa, K. K. (NASA Ames Research Center Moffett Field, CA, United States)
Wray, A. A. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
A-8271
NASA-TP-1769
Accession Number
81N16977
Funding Number(s)
PROJECT: RTOP 506-51-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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