Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to investigate the drag and stability characteristics of a series of flexible decelerator models. The models were tested at Mach numbers from 1.5 to 6 at dynamic pressures corresponding to pressure altitudes of 75,000 to 135,000 ft, respectively. Four basic decelerator configurations were examined: hyperflo parachutes at variable locations aft of three forebody models, hemisflo parachutes with varied amounts of canopy inlet reefing, a tandem configuration composed of a hyperflo parachute inside the suspension lines of a hemisflo parachute, and a conical ballute decelerator. (Author)


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    Title :

    Wind Tunnel Investigation of Flexible Aerodynamic Decelerator Characteristics at Mach Numbers 1.5 to 6


    Contributors:

    Publication date :

    1965


    Size :

    37 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English