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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    Title :

    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


    Contributors:

    Publication date :

    1974


    Size :

    59 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English