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A flight and wind tunnel investigation of the effect of angle-of-attack rate on maximum lift coefficientWind tunnel tests to determine effect of angle of attack on maximum lift at stall for half-wing models, and single engine, jet propelled aircraft
Document ID
19650026226
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Conner, F.
Twomey, W.
Willey, C.
Date Acquired
August 2, 2013
Publication Date
October 1, 1965
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-321
Report Number: NASA-CR-321
Accession Number
65N35827
Funding Number(s)
CONTRACT_GRANT: NAS4-471
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
JET AIRCRAFT
ANGLE OF ATTACK
WIND TUNNEL STABILITY TEST

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