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 the 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 shockwave and the body. The Sauer graphical-numerical iteration method was used for the remainder of the solution.
Preliminary calculations and the work for Mach number 3 were carried out by Dr. H. K. Forster to whom we are indebted for instruction and aid with this work
