These tests were conducted to obtain longitudinal stability and control data for Mach numbers from 0.35 to 1.2. Data were obtained for an alpha range of -2 deg to +22 deg at beta = 0 deg. The effect of speedbrake deflection and body flap deflection was obtained through the Mach range. Boundary layer transition strips were used on the model. (Author)


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    Title :

    Wind Tunnel Tests of an 0.015-Scale Configuration 140A/B Space Shuttle Orbiter Model (67-0) in the NASA/Lrc 8-Foot Tpt to Obtain Transonic Aerodynamic Force Data (OA106)


    Contributors:
    R. Burrows (author)

    Publication date :

    1974


    Size :

    197 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English