SUBSONIC WIND-TUNNEL INVESTIGATION OF ERRORS INDICATED BY TOTAL-PRESSURE TUBES IN THE FLOW FIELD OF A BODY SIMULATING THE NOSE OF THE X-15 RESEARCH AIRPLANE
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC
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A wind-tunnel investigation was conducted to determine the source of errors exhibited by a secondary total-pressure tube located on the upper surface of the fuselage of the X-15 with the nose boom. The effects of model- nose configuration, of the meridian plane of the totalpressure measurements, of changes in Mach numbers, and of the addition of a transition strip were investigated. Results indicated that a model configuration employing a nose boom suffered large losses of total pressure on the upper surface of the model. These errors were presumed to result from the vorticity shed by the boom. Results indicated the lower surface would be a suitable circumferential location for the secondary total-pressure tube. Effects of increasing the Mach number from 0.60 to 0.80 and the effects of adding a transition strip to the configuration with a nose boom were negligible. Wind-tunnel measurements were in reasonable agreement with flight measurements of secondary-tube total pressures for configurations without and with nose booms.
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