An application of the method of characteristics to axially symmetric supersonic flow

Abstract

The method of characteristics for three dimensional axially symmetric bodies was used to determine the velocity distribution about the nose of the Corporal E rocket, a rocket projectile, for Mach numbers 2 and 4. From the velocities the pressure distribution was determined and a drag coefficient computed. For a starting point eh nose of the projectile was approximated for a short distance by a cone and the Taylor-Maccoll solution to this problem was used. This solution gave the angle of shockware and the body. The Sauer graphical-numerical iteration method was used for the remainder of the solution. Preliminary calculation and the work for Mach number3 were carried out by Dr. H. K. Forster to whom we are indebted for instruction and aid with this work.