Pressure distribution and damping in steady pitch at supersonic Mach numbers of flat swept-back wings having all edges subsonic

Harold J. Walker, Mary B. Ballantyne
naca-tn-2197
Oct 1950


A method is presented for calculating the pressure distribution and damping in steady pitch at supersonic Mach number of thin, flat, swept-back wings having all edges straight and subsonic. Although it is adaptable to wings with negative rake at the tips, the method is applied only to wings with streamwise tips.

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