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Determination of corrections to flow direction sensor measurements over an angle-of-attack range from 0 degree to 85 degreesAn investigation was conducted into the nature of corrections for angle-of-attack and angle-of-sideslip measurements obtained with sensors mounted in front of each wingtip of a general aviation airplane. These flow corrections have been obtained from both wind-tunnel and flight tests over an angle-of-attack range from 0 to 85 deg. Both the angle-of-attack and angle-of-sideslip flow corrections were found to be substantial. The corrections were a function of the angle of attack and angle of sideslip and were fairly insensitive to configuration changes and rotational effects. The angle-of-attack flow correction determined from the static wind-tunnel tests agreed reasonably well with the correction determined from flight tests.
Document ID
19860004797
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Moul, T. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1985
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
L-15759
NAS 1.15:86402
NASA-TM-86402
Accession Number
86N14267
Funding Number(s)
PROJECT: RTOP 505-45-43-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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