NACA Technical Notes

Abstract

Report presenting an analysis to determine the pressure distribution, span loading, and rolling moment due to small angles of sideslip at supersonic speeds for a series of thin, sweptback, tapered wings with wing tips parallel to the axis of wing symmetry. Three basic series of Mach numbers and plan-form combinations are considered, all of which have supersonic trailing edges in conjunction with both leading edges subsonic, one leading edge subsonic and one leading edge supersonic, and both leading edges supersonic