CALIBRATION OF THE SHOCK TUNNEL COMPONENT OF COUNTERFLOW RANGE (I) AT MACH 7.5
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Calibration of the shock tunnel component of the Counterflow Range I operating with a new nozzle throat designed to yield Mach 7.5 is reported. Transverse pitot-pressure profiles and heat-transfer rates on a hemisphere-cylinder model in the test section were measured at four flow conditions. A single probe was traversed along the nozzle centerline to determine the streamwise pitot-pressure gradient. Shock detachment distances for a hemisphere-cylinder were measured to determine when helium from the shock tunnel driver entered the test section. Results from these tests indicate a repeatable test core of uniform flow having a 12.5-in. diameter. Test times of from 2.5 to 4 msec were recorded before large quantities of helium appeared to be entering the test section. The streamwise pressure measurements indicated a Mach number gradient of 0.2ft.
- Test Facilities, Equipment and Methods
- Fluid Mechanics