Assumptions underlying application of shock expansion theory to calculation of pressure distribution on thin sharp nosed 2-dimensional airfoil in supersonic stream examined, and it is suggested that they might be expected to lead to appreciable errors when Mach Number is large; this case is examined by use of " hypersonic analogy".
Critique of shock-expansion theory
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 22 , n 10 ; p 673-680 + 720
1955
Aufsatz (Zeitschrift)
Englisch
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