WIND-TUNNEL TESTS OF SEVEN STATIC-PRESSURE PROBES AT TRANSONIC SPEEDS

Wind-tunnel tests were conducted to determine the errors of seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 andAT ANGLES OF ATTACK FROM -1.7 TO 8.4 DEGREES. The test Reynolds...

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Bibliographic Details
Main Author: CAPONE,FRANCIS J
Format: Report
Language:English
Subjects:
AERODYNAMIC CHARACTERISTICS
AERODYNAMIC CONFIGURATIONS
BODIES OF REVOLUTION
CONICAL BODIES
ERRORS
INSTRUMENTATION
MEASUREMENT
MODEL TESTS
PITOT TUBES
PRESSURE
TRANSONIC CHARACTERISTICS
TRANSONIC WIND TUNNELS
WIND TUNNEL MODELS
WIND TUNNELS
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Summary:Wind-tunnel tests were conducted to determine the errors of seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 andAT ANGLES OF ATTACK FROM -1.7 TO 8.4 DEGREES. The test Reynolds number per foot varied from 3.35 to 4.05 times 10 to the 6th power. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at plus or minus degrees from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of freestream static pressure through the test angle-ofattack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of freestream static pressure. (Author)