Wind tunnel tests were conducted to determine the aerodynamic interference between the space shuttle orbiter, external tank, and solid rocket booster on a 0.004 scale ascent configuration. Six component aerodynamic force and moment data were recorded over an angle of attack range from minus 10 to plus 10 degrees at zero degree sideslip. A sideslip range of minus 10 to plus 10 degrees at zero degree angle of attack was also tested. The Mach number range was varied from 0.6 to 4.96 with Reynolds number varying between 4.9 and 6.8 times one million per foot. (Author)


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    Title :

    Space Shuttle Determination of the Aerodynamic Interference Between the Space Shuttle Orbiter, External Tank, and Solid Rocket Booster on a 0.004 Scale Ascent Configuration


    Contributors:
    P. Ramsey (author) / R. Buchholz (author) / E. Allen (author) / J. Dehart (author)

    Publication date :

    1973


    Size :

    926 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English