Griffing, Charles W. and Wilburn, William Clarence and Purdon, David and McLaughlin, Earl Wilson (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)|
|Subject Keywords:||Aeronautical Engineering|
|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:||27 Jan 2017 21:33|
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