Experimental aerodynamic investigations were conducted in the NASA/Langley unitary plan wind tunnel on a sting mounted 0.010-scale outer mold line model of the 140A/B configuration of the Rockwell International Space Shuttle Vehicle. The primary test objectives were to obtain: (1) six component force and moment data for the mated vehicle at subsonic and transonic conditions, (2) effects of configuration build-up, (3) effects of protuberances, ET/orbiter fairings and attach structures, and (4) elevon deflection effects on wing bending moment. Six component aerodynamic force and moment data and base and balance cavity pressures were recorded over Mach numbers of 1.6, 2.0, 2.5, 2.86, 3.9, and 4.63 at a nominal Reynolds number of 20 to the 6th power per foot. Selected configurations were tested at angles of attack and sideslip from -10 deg to +10 deg. For all configurations involving the orbiter, wing bending, and torsion coefficients were measured on the right wing. (Author)


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    Title :

    Results of Investigations of an 0.010-Scale 140A/B Configuration (Model 72-Ots) of the Rockwell International Space Shuttle Orbiter in the NASA/Langley Research Center Unitary Plan Wind Tunnel


    Contributors:

    Publication date :

    1975


    Size :

    455 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English