An application of the method of characteristics to axially symmetric supersonic flow
Griffing, Charles Wing
Wilburn, William Clarence
McLaughlin, Earl Wilson
Forster, H. K.
Stewart, H. J.
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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.
This thesis document was issued under the authority of another institution, not NPS. At the time it was written, a copy was added to the NPS Library collection for reasons not now known. It has been included in the digital archive for its historical value to NPS. Not believed to be a CIVINS (Civilian Institutions) title.
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