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)
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
1974
59 pages
Report
Keine Angabe
Englisch
Uncertainty Analysis of the NASA MSFC 14-Inch Trisonic Wind Tunnel
British Library Conference Proceedings | 1999
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