Effect of a finite trailing-edge thickness on the drag of rectangular and delta wings at supersonic speeds

E. B. Klunker, Conrad Rennemann, Jr.
naca-tn-2828
Nov 1952


The effect of a finite trailing-edge thickness on the pressure drag of rectangular and delta wings with truncated diamond-shaped airfoil sections with a given thickness ratio is studied for supersonic Mach number, linearized theory being used to evaluate the surface pressures.

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