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Support-sting interference on boattail pressure drag for Reynolds numbers up to 70 x 10 to the 6thA model was tested in the Langley 0.3-Meter Transonic Cryogenic Tunnel to investigate the effects of Reynolds number on boattail pressure drag for a variety of sting shapes. The boattail pressure drag for constant Mach number increased linearly with Reynolds number over the Reynolds number range tested. The data indicated that, as the disturbance produced by the sting on the boattail increased, the boattail pressure drag became less sensitive to Reynolds number change. Also, it was found that the model base pressure versus Reynolds number curve reached a plateau within the Reynolds number range examined.
Document ID
19830035469
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gloss, B. B.
(NASA Langley Research Center Hampton, VA, United States)
Sewall, W. G.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 83-0387
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting
Location: Reno, NV
Start Date: January 10, 1983
End Date: January 13, 1983
Accession Number
83A16687
Distribution Limits
Public
Copyright
Other

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