Details are presented of flow visualization techniques developed during wind tunnel test IA-52 conducted in a 14 x 14 inch trisonic wind tunnel. Testing was conducted from Mach = 0.9 to 5.0 on the orbiter alone and integrated vehicle configurations. Thin film oil paint and ultraviolet light sensitive oil applications were used on a .004 scale model vehicle. Test results presented are in the form of black and white photographs taken after the completion of a test run. (Author)


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    Titel :

    Results of Flow Visualization Studies in the NASA/Msfc 14 X 14 Inch Trisonic Wind Tunnel on a .004 Scale Model (34-0) Space Shuttle Orbiter and Integrated Vehicle


    Beteiligte:
    W. P. Garton (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    59 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch