Supersonic Wind Tunnel Tests of Two Rocket Propelled Projectile Models

Authors: Fossier, Mike Walter; Small, John

Year: 1947

Degree: Engineer's thesis

Advisor: Puckett, Allen E.

Committee Member: Unknown, Unknown

Option: Aeronautics

DOI: 10.7907/71EK-W641

Abstract

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.

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