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
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Force Tests on a Separable-Nose Crew Escape Capsule in Proximity to the Parent Fuselage with Cold Flow Rocket Plume Simulation at Mach Numbers 2 Through 5
Static force tests were conducted on a separable-nose crew escape capsule in the presence of the forward section of the airplane fuselage. The capsule escape rocket jet plume was simulated with air heated to a total temperature of approximately 100F. Data were obtained at Mach numbers from 2 through 5 at capsule angles of attack from -15 to 25 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 at a fuselage angle of attack and angle of sideslip of zero. Reynolds number, based on a model length of 18.1 in., ranged from 5,700,000 to 12,300,000. Results are presented showing the effects of the fuselage section on the aerodynamic characteristics of the capsule, with and without simulation of the escape rocket exhaust plume. (Author).
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
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. (Author).
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
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. (Author).