Aerodynamic Characteristics of an Ejection Seat Escape System with Cold Flow Rocket Plume Simulation at Mach Numbers from 0.6 through 1.5.
Final rept. 19 Jun-3 Jul 1969
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A test was conducted in a transonic wind tunnel to determine the aerodynamic characteristics of a 0.5-scale ejection seat escape system with a dummy crew member attached during simulated rocket-off and rocket-on conditions. Results were obtained at free-stream Mach numbers of 0.6, 0.9, 1.2, and 1.5 through a model angle-of-attack range of 360 deg and model yaw angles up to 45 deg. High pressure air was used to simulate the escape rocket jet plume at altitudes from sea level to 40,000 ft.
- Fluid Mechanics