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Wind-tunnel investigation of the flow correction for a model-mounted angle of attack sensor at angles of attack from -10 deg to 110 degA preliminary wind tunnel investigation was undertaken to determine the flow correction for a vane angle of attack sensor over an angle of attack range from -10 deg to 110 deg. The sensor was mounted ahead of the wing on a 1/5 scale model of a general aviation airplane. It was shown that the flow correction was substantial, reaching about 15 deg at an angle of attack of 90 deg. The flow correction was found to increase as the sensor was moved closer to the wing or closer to the fuselage. The experimentally determined slope of the flow correction versus the measured angle of attack below the stall angle of attack agreed closely with the slope of flight data from a similar full scale airplane.
Document ID
19800005854
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Moul, T. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1979
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TM-80189
Accession Number
80N14110
Funding Number(s)
PROJECT: RTOP 505-41-13-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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