Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tips : subsonic leading edges

On the basis of linearized supersonic flow theory, the lateral force and yawing moment due to combined angle of attack and rolling have been evaluated for families of thin sweptback tapered wings with streamwise tips. Equations were derived for wings that are contained between the Mach cones springing from the wing apex and from the trailing edge of the root section, that is, wings with subsonic leading edges and supersonic trailing edges. Some calculations, based on these equations, are included for groups of wings with subsonic trailing edges. Design charts are presented which permit estimation of certain stability derivatives for given values of Mach number, aspect ratio, taper ratio, and leading edge sweep. Some illustrative variations of the derivatives with these parameters are also included. All numerical data are presented relative to a body-axes system with moments taken about the wing apex. For convenience in application, formulas are given for transforming from this system to a stability-axes system with moments taken about an arbitrary point.