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Pressure distributions on a flat-plate delta wing swept 65 deg at a Mach number of 5.97 at angles of attack from 65 deg to 115 deg and angles of roll from 0 deg to 25 deg at a 90 deg angle of attackPressure distributions on flat plate delta wing swept 65 deg at hypersonic speeds at angles of attack from 65 deg to 115 deg and angles of roll from 0 deg to 25 deg at 90 deg angle of attack
Document ID
19660024037
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Goldberg, T. J. (NASA Langley Research Center Hampton, VA, United States)
Hondros, J. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1962
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-X-702
Report Number: NASA-TM-X-702
Accession Number
66N33327
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
ANGLE OF ATTACK
PRESSURE DISTRIBUTION
DELTA WING
HYPERSONIC SPEED
SWEPT WING
FLAT PLATE

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