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Investigation of solid plume simulation criteria to produce flight plume effects on multibody configuration in wind tunnel testsAn investigation to determine the sensitivity of the space shuttle base and forebody aerodynamics to the size and shape of various solid plume simulators was conducted. Families of cones of varying angle and base diameter, at various axial positions behind a Space Shuttle launch vehicle model, were wind tunnel tested. This parametric evaluation yielded base pressure and force coefficient data which indicated that solid plume simulators are an inexpensive, quick method of approximating the effect of engine exhaust plumes on the base and forebody aerodynamics of future, complex multibody launch vehicles.
Document ID
19860012036
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Frost, A. L.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Dill, C. C.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:2569
NASA-TP-2569
Accession Number
86N21507
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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