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

by Griffing, C. W.

Abstract (Summary)
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.
Bibliographical Information:

Advisor:Homer Joseph Stewart

School:California Institute of Technology

School Location:USA - California

Source Type:Master's Thesis

Keywords:aeronautics

ISBN:

Date of Publication:01/01/1947

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