An F-104B airplane was modified to investigate the drag and stability characteristics of a ballute decelerator in the wake of an asymmetrical airplane. Decelerator deployments were initiated at a Mach number of 1.3 and an altitude of 15,240 meters (50,000 feet) and terminated when the airplane had decelerated to a Mach number of 0.5. The flight tests indicated that the decelerator had a short inflation time with relatively small opening forces. The drag levels attained with the subject decelerator were less than those obtained with other high-speed decelerators behind a symmetrical tow vehicle. The ballute demonstrated good stability characteristics behind the testbed airplane.


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    Title :

    Performance of a ballute decelerator towed behind a jet airplane


    Contributors:
    Pyle, J. S. (author) / Phelps, J. R. (author) / Baron, R. S. (author)

    Publication date :

    1973-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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