The base pressure environment was investigated for the first and second stage mated vehicle in a supersonic flow field from Mach 1.55 through 2.20 with simulated rocket engine exhaust plumes. The pressure environment was investigated for the orbiter at various vent port locations at these same freestream conditions. The Mach number environment around the base of the model with rocket plumes simulated was examined. Data were obtained at angles of attack from -4 deg through +4 deg at zero yaw, and at yaw angles from -4 deg through +4 deg at zero angle of attack, with rocket plume sizes varying from smaller than nominal to much greater than nominal. Failed orbiter engine data were also obtained. Elevon hinge moments and wing panel load data were obtained during all runs. Photographs of the tested configurations are shown. (Author)


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    Titel :

    Results of an Investigation of Jet Plume Effects on an 0.010-Scale Model (75-OTS) of the Space Shuttle Integrated Vehicle in the 9 X 7-Foot Leg of the NASA/Ames Unitary Wind Tunnel (IA82B), Volume 1


    Beteiligte:

    Erscheinungsdatum :

    1976


    Format / Umfang :

    869 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch