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Roll-control effectiveness, of several spoiler configurations on an airplane model with wing sweep of 55 deg and 75 deg at supersonic Mach numbersRoll-control effectiveness of spoiler configurations on aircraft model with variable sweep wings at supersonic speeds
Document ID
19710010651
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hayes, C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1971
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-2165
L-7177
Report Number: NASA-TM-X-2165
Report Number: L-7177
Accession Number
71N20126
Funding Number(s)
CONTRACT_GRANT: 720-01-11-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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