A pressure-distribution investigation of a body of revolution has been conducted in the Langley 4- by 4-foot supersonic tunnel at a Mach number of 1.59 and a Reynolds number of 1.04 x 106 per foot. The data over the forward part of the body have been analyzed to indicate the. accuracy with which an uncalibrated cone containing four static-pressure orifices and one total-pressure orifice can be used as a Mach number and flow-angle indicator at supersonic speeds. The results show that, by a simple averaging process, the free-stream Mach number for the present tests was predicted within 0.01 up to incidence angles of about 8°. Further increases in incidence resulted in the overestimation of the Mach number by as much as 0.05 at an angle of 16.10°. The angle of attack and the angle of yaw were predicted within 0.5° for various combinations of pitch and yaw up to an angle of attack of 10°. In an installation where the yaw was zero, the angle-of-attack prediction was improved to within 0.3° in the angle-of-attack range from 6° to 14° by proper orien¬tation of the static orifices.
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