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Space shuttle afterbody aerodynamics/plume simulation data summaryA series of parametric wind tunnel tests was conducted to provide a base for developing a simulation of afterbody/base aerodynamics for multibody/multibase rocket-powered vehicles (such as Space Shuttle) which use unheated air as the simulant gas in development wind tunnel tests. The tests described were parameterized on external configuration, nozzle internal configuration, base geometry, propulsion gas type, and freestream Mach number (0.5 to 3.5). The tests were conducted over a 4-year period. Presented in this report are the data and pertinent reference information necessary to perform an analysis which would lead to a simulation procedure. The type of data obtained during the tests described herein include model base afterbody, and nozzle internal surface static pressure distributions, model chamber pressure and temperature, and freestream conditions. Also included is a brief description of simulation procedures that were used by the Space Shuttle program.
Document ID
19790009639
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Blackwell, K. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Hair, L. M.
(REMTECH, Inc., Huntsville Ala., United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1384
M-276
Accession Number
79N17810
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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