Theoretical stability derivatives of thin sweptback wings tapered to a point with sweptback or sweptforward trailing edges for a limited range of supersonic speeds

The stability derivatives valid for a limited range of sqersonic speeti are presented for a series of sweptback wings tapered to a petit with sweptback or sweptforwsmi trailhg.edges.These Wngs were derived by modifying the trailtig edge of a basic triangular wing so that it coincided with lines drawn frm the wing tips to the wing axis of symmetry.The stability derivatives were formulated by us-the pressure distributions previously obtained for tie basic triangular wing for aqjl.eofattack, sideslip, pitching, rolling, and yawing.Explicit expressions are given for the stability derivatives with respect to principal body axes and cmmersion formulas are provided for the tramfommtion to stability axes.The results are limited to Wch numbers for which the wing is contained within the Mach cones springing fram the vertex end from the trailing edge of the center section of the wing.I ---...