Publication Date:
2019-06-27
Description:
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.
Keywords:
SPACE VEHICLES
Type:
NASA-CR-134087
,
DMS-DR-2042
Format:
application/pdf