CORNELL UNIV ITHACA NY GRADUATE SCHOOLOF AEROSPACE ENGINEERING
The method of expansion in powers of a thickness parameter is employed to calculate supersonic, inviscid flow about symmetrical arrow-head wings lying entirely within the tip Mach cone. In this method, the first order terms constitute the familiar, linearized Prandtl-Glauert approximation. The method is one of iteration. Here the second approximation is computed and plotted for a family of arrow-head wings having various leading-edge angles and thicknesses, and flying at various Mach numbers. It is necessary to use Lighthills method to determine the strength of the attached conical shock.