Airfoil profiles for minimum pressure drag at supersonic velocities : application of shock-expansion theory, including consideration of hypersonic range

Dean R. Chapman
naca-tn-2787
Sep 1952

A theoretical investigation is made of airfoil profiles at supersonic velocities to determine the shapes having minimum pressure drag at zero lift for various given auxiliary conditions. Shock-expansion theory is employed, thereby extending the applicability of the results through the hypersonic range.

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