The primary objective of the test was to determine the aerodynamic increments due to the attach structure. Secondary objectives were to determine the effects of: (1) orbiter nose mold line changes; (2) wire bundle fairings on data measurements; and (3) flow angularity. The scale model was tested over the Mach range from 0.60 to 1.25 at angles of attack and sideslip from -8 to +8 deg. The total pressure was 22 psia for all runs. Six-component orbiter data were obtained from a balance in the orbiter which was sting supported. The external tank was attached to the solid rocket booster, each of which was sting supported. An alternate two sting/two balance arrangement was also tested with a single sting and balance in the external tank measuring combined ET/SRB aero data replacing the two stings in the SRB's. Two runs were also made at Mach number 4.96 with the two SRB's removed. The aerodynamic coefficients obtained are tabulated as a function of angle of attack or sideslip for each Mach number value.


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    Titel :

    Results of Transonic Tests in the NASA/MSFC 14-Inch Trisonic Wind Tunnel on a 0.004-Scale Model (74-Ots) Space Shuttle Launch Vehicle (FA25)


    Beteiligte:
    T. E. Lundy (Autor:in)

    Erscheinungsdatum :

    1979


    Format / Umfang :

    375 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch