Pressure distribution and damping in steady roll at supersonic Mach numbers of flat swept-back wing with subsonic edges

Harold J. Walker, Mary B. Ballantyne
naca-tn-2047
Mar 1950


A method, which is based upon the concept of the superposition of conical and quasi-conical flows, is presented for calculating the pressure distribution and damping in steady roll at supersonic Mach numbers of thin, flat, swept-back wings having all edges straight and subsonic. Although it can be adapted to wings having negative rake at the tips, the method is developed only for wings having negative rake at the tips, the method is developed only for wings with streamwise tips.

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