1950•Unpublished venueRequires access
Pressure distribution and damping in steady roll at supersonic Mach numbers of flat swept-back wing with subsonic edges
H. J. Walker, Mary B Ballantyne
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Abstract
Note presenting a method for calculating the pressure distribution and damping in steady roll at supersonic Mach numbers of thin, flat, sweptback wings with all edges straight and subsonic. It can be adapted to wings with negative rake at the tips, but the method is developed only for wings with streamwise tips.