Supersonic wind tunnel tests of two rocket propelled projectile models

• Main Authors: Fossier, Mike Walter, Small, John
• Format: Others
• Published: 1947
• Online Access: https://thesis.library.caltech.edu/4910/1/Fossier_m_1947.pdf; 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. https://resolver.caltech.edu/CaltechETD:etd-12092008-082853 <https://resolver.caltech.edu/CaltechETD:etd-12092008-082853>

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.