Pressure distribution test data obtained on a 0.10-scale model of the forward fuselage of the Space Shuttle Orbiter are presented without analysis. The tests were completed in the AEDC 16T Propulsion Wind Tunnel. The 0.10-scale model was tested at angles of attack from -2 deg to 18 deg and angles of side slip from -6 to 6 deg at Mach numbers from 0.25 to 1/5 deg. The tests were conducted in support of the development of the Shuttle Entry Air Data System (SEADS). In addition to modeling the 20 SEADS orifices, the wind-tunnel model was also instrumented with orifices to match Development Flight Instrumentation (DFI) port locations that existed on the Space Shuttle Orbiter Columbia (OV-102) during the Orbiter Flight Test program. This DFI simulation has provided a means of comparisons between reentry flight pressure data and wind-tunnel and computational data.


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    Titel :

    Pressure Distributions Obtained on a 0.10-Scale Model of the Space Shuttle Orbiter's Forebody in the AEDC 16T Propulsion Wind Tunnel


    Beteiligte:
    P. M. Siemers (Autor:in) / M. W. Henry (Autor:in)

    Erscheinungsdatum :

    1986


    Format / Umfang :

    442 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch