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Drag reduction of the Space ShuttleWind-tunnel and water-tunnel experiments are conducted to determine which factors contribute to the base-pressure drag experienced by the Space Shuttle Orbiter. Testing is conducted on a 4.05-percent scale model in the TAMU Water Tunnel and Low Speed Wind Tunnel with passive near-wake flow-modification devices attached in some of the tests. The devices are evaluated on the basis of effectiveness in terms of increasing the base pressure. Base pressures increase when a base cavity is introduced; a smooth cavity increases pressure by 13 percent, and when v-grooves are introduced into the cavity the pressure increases by 19 percent. When the v-groove base cavity is combined with a fairing plate, the total base pressure reaches 25 percent. The experimental results suggest that the base drag of the Space Shuttle Orbiter can be effectively reduced by the use of a base-cavity mechanism.
Document ID
19910069112
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ahmed, Anwar
(Texas A & M University College Station, United States)
Javed Khan, Mohammad
(Texas A&M Univ. College Station, TX, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-3212
Accession Number
91A53735
Funding Number(s)
CONTRACT_GRANT: NAS9-18261
Distribution Limits
Public
Copyright
Other

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