Approximate theories for supersonic and hypersonic flow over bodies of revolution at zero angle of attack are appraised by comparison with characteristics and second-order results, using hypersonic similarity as basis; combination of second-order supersonic and second-order shock-expansion theory provides good results; summary design curves give pressure drag of conical and ogive noses and boattails over transonic, supersonic, and hypersonic Mach numbers.
Summary of supersonic pressure drag of bodies of revolution
J Aerospace Sciences
Journal of Aerospace Science ; 28 , n 7
1961
10 pages
Article (Journal)
English
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