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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    Titel :

    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)


    Beteiligte:
    M. T. Petrozzi (Autor:in) / M. D. Milam (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    397 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch