Experimental aerodynamic investigations were conducted in NASA/Langley 8-Foot transonic pressure tunnel on a sting mounted 0.010-scale outer mold line model of 104A/B configuration of the Rockwell International space shuttle vehicle. Component aerodynamic force and moment data and base and balance cavity pressures were recorded over an angle of attack range of -10 deg to +10 deg at Mach numbers of 0.6, 0.8, 0.9, 0.98, 1.13, and 1.2. Selected configurations were tested at sideslip angles from -10 deg to +10 deg. For all configurations involving the orbit, wing bending and torsion were measured on the right wing. Inboard elevon setting of 0 deg, +4 deg and +8 deg and outboard settings of 0 deg, +4 deg and +8 deg were tested. (Author)


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    Title :

    Results of Transonic Wind Tunnel Tests on an 0.010-Scale Space Shuttle Mated Vehicle Model 72-Ots in the Larc 8-Foot Tpt (IA43)


    Contributors:

    Publication date :

    1975


    Size :

    397 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English