Tabulated data of an experimental investigation are presented which was conducted in the AEDC/VKF Tunnel B to obtain interaction effects of RCS thruster jet plumes on SSV aerodynamics during staging to simulate RTLS abort. Interaction effects of the orbiter RCS thruster jet plumes on the orbiter and ET aerodynamics were investigated. RCS thruster jet plumes were simulated using both air and a 15 percent argon 85 percent helium gas mixture. The ET angle of attack range was -40 to +25 deg at sideslip angles of 0, 3, and 6 degrees. Orbiter angle of attack was varied from -15 to +10 degrees at sideslip angles of 0 and 3 deg. External tank full scale separation distances simulated were 0 to 1400 in. axially; 0 to 54 in. laterally; and a range of -100 to 1000 in. vertically. Data were also obtained on the ET in the interference-free flow field. Quiescent (no tunnel flow) thruster plume interaction data were obtained on the orbiter and orbiter-ET combination. Tests were conducted at Mach number 6 and a Reynolds number of 0.86 million per foot.


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    Titel :

    Results of Tests Using a 0.0125-Scale Model (70-QT) of the Space Shuttle Vehicle Orbiter in the AEDC Vkf Tunnel B (IA22), Volume 2


    Beteiligte:
    J. J. Daileda (Autor:in) / J. Marroquin (Autor:in)

    Erscheinungsdatum :

    1977


    Format / Umfang :

    620 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch