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
01.02.1976
Sonstige
Keine Angabe
Englisch
ICAS2014_0181: NOSES OF MINIMAL WAVE DRAG IN SUPERSONIC FLOW
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