Griffing, C. W. (1947) An application of the method of characteristics to axially symmetric supersonic flow. Engineer's thesis, California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-12082008-150626
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.
|Item Type:||Thesis (Engineer's thesis)|
|Degree Grantor:||California Institute of Technology|
|Division:||Engineering and Applied Science|
|Thesis Availability:||Public (worldwide access)|
|Defense Date:||1 January 1947|
|Default Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Imported from ETD-db|
|Deposited On:||24 Dec 2008|
|Last Modified:||26 Dec 2012 03:12|
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