It is shown that the drag of any semi-infinite airfoil section in purely subsonic inviscid flow follows precisely the Prandtl-Glauert compressibility rule. The result for the parabola has application to leading edge corrections in thin airfoil theory.
The compressibility rule for drag of airfoil noses
1976-02-01
Miscellaneous
No indication
English
ICAS2014_0181: NOSES OF MINIMAL WAVE DRAG IN SUPERSONIC FLOW
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