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)


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    Title :

    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


    Contributors:
    E. A. Price (author)

    Publication date :

    1970


    Size :

    79 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English