Investigation to determine performance of simple thin airfoils with aid of nonlinear transonic theory first developed by T.vonKARMAN; expressions for pressure coefficient across oblique shock and Prandtl-Meyer expansion are developed in terms of transonic similarity parameter; aerodynamic coefficients calculated in similarity form for flat plate and asymmetric wedge airfoils, and curves are plotted.
Airfoils in slightly supersonic flow
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 16 , n 1
1949
7 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Supersonic low-density flow over airfoils
AIAA | 1989
|Supersonic low-density flow over airfoils
AIAA | 1989
|Inviscid flow about airfoils at high supersonic speeds
TIBKAT | 1952
|Inviscid flow about airfoils at high supersonic speeds
Engineering Index Backfile | 1952
|