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Wind-tunnel calibration and requirements for in-flight use of fixed hemispherical head angle-of-attack and angle-of-sideslip sensorsWind-tunnel tests were conducted with three different fixed pressure-measuring hemispherical head sensor configurations which were strut-mounted on a nose boom. The tests were performed at free-stream Mach numbers from 0.2 to 3.6. The boom-angle-of-attack range was -6 to 15 deg, and the angle-of-sideslip range was -6 to 6 deg. The test Reynolds numbers were from 3.28 million to 65.6 million per meter. The results were used to obtain angle-of-attack and angle-of-sideslip calibration curves for the configurations. Signal outputs from the hemispherical head sensor had to be specially processed to obtain accurate real-time angle-of-attack and angle-of-sideslip measurements for pilot displays or aircraft systems. Use of the fixed sensors in flight showed them to be rugged and reliable and suitable for use in a high temperature environment.
Document ID
19730009287
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Montoya, E. J.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-6986
H-702
Report Number: NASA-TN-D-6986
Report Number: H-702
Accession Number
73N18014
Funding Number(s)
PROJECT: RTOP 761-74-01-00-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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