THEORETICAL CALCULATION OF THE PRESSUREnDISTRIBUTION, SPAN LOADING, AND ROLLING MOMENTnDUE TO SIDESLIP AT SUPERSONIC SPEEDS FOR THIN SWEPTBACKnTAPERED WINGS WITH SUPERSONIC TRAILING EDGES ANDnWING TIPS PARALLEL TO THE AXIS OF WING SYMMETRY

摘要

On the basis of linearized supersonic-flow theory, an analysis was undertaken 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 number and plan-form combinations are considered, all of which have supersonic trailing edges in conjunction with one of the following: (a) both leading edges sub¬sonic, (b) one leading edge subsonic and one leading edge supersonic, and (c) both leading edges supersonic. In addition to the Mach number limitation resulting from the supersonic-trailing-edge condition, the tip Mach lines may not intersect on the wing.nResults obtained for the configuration with both leading edges sub¬sonic include formulas for the pressure distribution, span loading, rolling moment, and the corresponding stability derivative C. For configurations with a supersonic leading edge, formulas for the pressure distribution are presented.