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Evaluation of a flow direction probe and a pitot-static probe on the F-14 airplane at high angles of attack and sideslipThe measurement performance of a hemispherical flow-angularity probe and a fuselage-mounted pitot-static probe was evaluated at high flow angles as part of a test program on an F-14 airplane. These evaluations were performed using a calibrated pitot-static noseboom equipped with vanes for reference flow direction measurements, and another probe incorporating vanes but mounted on a pod under the fuselage nose. Data are presented for angles of attack up to 63, angles of sideslip from -22 deg to 22 deg, and for Mach numbers from approximately 0.3 to 1.3. During maneuvering flight, the hemispherical flow-angularity probe exhibited flow angle errors that exceeded 2 deg. Pressure measurements with the pitot-static probe resulted in very inaccurate data above a Mach number of 0.87 and exhibited large sensitivities with flow angle.
Document ID
19840012446
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Larson, T. J. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
March 1, 1984
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TM-84911
NAS 1.15:84911
H-1189
Accession Number
84N20514
Funding Number(s)
PROJECT: RTOP 505-31-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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