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Effects of angle of attack and nose bluntness on the hypersonic flow over cones.Nose bluntness and angle of attack effects on hypersonic flow, noting shock wave deflection decrease of minimum possible shock angle, varying specific heat ratio, convective heating, boundary layer transition, etc
Document ID
19660054349
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cleary, J. W.
Date Acquired
August 3, 2013
Publication Date
June 1, 1966
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 66-414
Report Number: AIAA PAPER 66-414
Accession Number
66A33639
Distribution Limits
Public
Copyright
Other
Keywords
SPECIFIC HEAT
BLUNT BODY
HYPERSONIC FLOW
SHOCK WAVE
BOUNDARY LAYER TRANSITION
ANGLE OF ATTACK

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