Considerations of cruise-back efficiency and subsonic flying qualities are shown to have resulted in a configuration with an aft high wing of moderate aspect ratio and with vertical tails located at the wing tips. The need to protect the air breathing engines during ascent and reentry and the desire for a low trim penalty longitudinal control surface led to consideration of a jet-flap canard. The advantages of this application of STOL technology to a space system are examined and the results of both wind tunnel tests and flight simulations are discussed. Since the use of the jet-flap canard concept offers the potential for a minimum weight vehicle, a proposed technology development program is outlined in order that the full benefit of this concept may be realized.


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    Title :

    Impact of subsonic aerodynamic considerations on a space shuttle booster configuration


    Contributors:


    Publication date :

    1972-02-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :