Inviscid rotational supersonic flow behind shock wave attached to sharp leading edge of airfoil is studied by transformation of coordinates which introduces Crocco stream function psi as independent variable; using expansions in power series of psi, iterative process is developed for determination of pressure distribution along airfoil surface.
On supersonic flow past thick airfoils
J Aero/Space Sciences
Journal of Aerospace Science ; 27 , n 7
1960
Aufsatz (Zeitschrift)
Englisch
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