Aeromechanical Properties of Ejection Seat Escape Systems
Final rept. Jun 1969-Jan 1972
AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
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Valid prediction of combat aircraft ejection seat performance has been impossible because of the lack of technical data on its basic physical properties and aerodynamic characteristics. Wind tunnel tests were conducted using a full scale F-101 ejection seat and a half scale F-106 ejection seat to determine the aerodynamic characteristics. Data were obtained at free stream Mach numbers of 0.2, 0.4, 0.6 and 0.8 for the full scale model and 0.6, 0.9, 1.2 and 1.5 for the half scale model. Angle of attack was varied from 0 to 360 degrees for the half scale model and -45 and 90 degrees for the full scale model. Yaw angles were varied from 0 to 45 degrees. The shape of the rocket catapult exhaust plume was simulated by using high pressure air.
- Escape, Rescue and Survival