Force Tests on a Separable-Nose Crew Escape Capsule in Proximity to the Parent Fuselage With Cold Flow Rocket Plume Simulation at Mach Numbers 0.3 Through 1.2
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Static force tests were conducted on a separable-nose crew escape capsule in the presence of the forward section of an airplane fuselage. The capsule escape rocket exhaust plume was simulated with high-pressure air heated to a total temperature of approximately 100F. Data were obtained at Mach numbers of 0.3, 0.6, 0.9, and 1.2 at capsule angles of attack from -15 to 22 deg and angles of sideslip from 0 to 15 deg for various positions of the capsule relative to the fuselage section. All testing was conducted with the fuselage at zero-degree angle of attack and zero-degree sideslip. Data were obtained both with and without rocket exhaust plume simulation.