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Supersonic Wind Tunnel Tests of Two Rocket Propelled Projectile Models


Fossier, Mike Walter and Small, John (1947) Supersonic Wind Tunnel Tests of Two Rocket Propelled Projectile Models. Engineer's thesis, California Institute of Technology. doi:10.7907/71EK-W641.


Two models of rocket propelled projectiles have been tested in the Galcit 2 1/2 inch supersonic wind tunnel at a Mach Number of 3.06, and angles of attack from 0° to 10°. Variations of lift, drag, pitching moment, and position of center pressure with angle of attack have been obtained for each model. A strain gage balance system, which was designed to measure the forces acting on the models was found to be entirely satisfactory for this purpose. The results were found to agree very closely with the small perturbation theory for supersonic flow.

Item Type:Thesis (Engineer's thesis)
Subject Keywords:Aeronautical Engineering
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Puckett, Allen E.
Thesis Committee:
  • Unknown, Unknown
Defense Date:1 January 1947
Record Number:CaltechETD:etd-12092008-082853
Persistent URL:
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:4910
Deposited By: Imported from ETD-db
Deposited On:07 Jan 2009
Last Modified:16 Mar 2023 20:03

Thesis Files

PDF (Fossier_m_1947.pdf) - Final Version
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