Experimental aerodynamic investigations were conducted in a 3.5-foot hypersonic wind tunnel. The model used for this test was a 0.010-scale of the Configuration 2 Space Shuttle Orbiter and the External Tank. Six-component aerodynamic force and moment data were recorded over an angle of attack range from -8 deg to +30 deg at 0 deg and 5 deg angles of sideslip. Data was also recorded during beta sweeps of -8 deg to +10 deg at angles of attack of -10 deg, 0 deg, and 30 deg. All testing was done at Mach 7.3. Various elevon, rudder and orbiter to external tank attaching structures and fairings were tested to determine longitudinal and lateral-directional stability characteristics. Non-metric exhaust plumes were installed during a portion of the testing to determine the effects of the main propulsion system rocket plumes. (Author)


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    Titel :

    Results of Investigations on a 0.010-Scale Model of the Configuration 3 Space Shuttle Orbiter and External Tank in the NASA/Ames Research Center 3.5-Foot Hypersonic Wind Tunnel (IA15)


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

    Erscheinungsdatum :

    1974


    Format / Umfang :

    123 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch