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Development of a three axis fluidic airspeed sensorA three axis fluidic airspeed sensor system has been fabricated and wind tunnel tested. The complete system consists of the fluidic sensor, air power supply and instrumentation and readout. The system is adapted to aircraft and requires only the standard aircraft 28V dc supply to function.
Document ID
19730001745
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Neradka, V. F. (Bowles Fluidics Corp. Silver Spring, MD, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1972
Subject Category
Instrumentation And Photography
Report/Patent Number
NASA-CR-112167
R-08-15-72
Report Number: NASA-CR-112167
Report Number: R-08-15-72
Accession Number
73N10472
Funding Number(s)
CONTRACT_GRANT: NAS1-11266
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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