An investigation has been conducted in the Langley 26-inch transonic blow-down tunnel at Mach numbers from 0.58 to 1.31 to examine some of the character¬istics of a differential-pressure system used to measure flow angles over the hemisphere-cone nose of the Ranger IV vehicle. The differential pressures were measured between two orifices located in the pitch plane at 45° off the center line of the hemisphere nose. The effects of variations in Mach number, Reynolds number, pitch angle, and combined pitch and yaw angles on the differential-pressure characteristics were studied.nThe results indicated that, for a given total pressure and Mach number, the differential pressure varied linearly with pitch angle and was unaffected by vari¬ations in Reynolds number and yaw angle within the range of this investigation. As Mach number increased above 1, a decreasing effect of afterbody shape was shown.
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