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Design and Flight Evaluation of a New Force-Based Flow Angle ProbeA novel force-based flow angle probe was designed and flight tested on the NASA F-15B Research Testbed aircraft at NASA Dryden Flight Research Center. The prototype flow angle probe is a small, aerodynamic fin that has no moving parts. Forces on the prototype flow angle probe are measured with strain gages and correlated with the local flow angle. The flow angle probe may provide greater simplicity, greater robustness, and better access to flow measurements in confined areas relative to conventional moving vane-type flow angle probes. Flight test data were obtained at subsonic, transonic, and supersonic Mach numbers to a maximum of Mach 1.70. Flight conditions included takeoff, landing, straight and level flight, flight at higher aircraft angles of attack, and flight at elevated g-loadings. Flight test maneuvers included angle-of-attack and angle-of-sideslip sweeps. The flow angle probe-derived flow angles are compared with those obtained with a conventional moving vane probe. The flight tests validated the feasibility of a force-based flow angle measurement system.
Document ID
20060007313
Acquisition Source
Armstrong Flight Research Center
Document Type
Technical Memorandum (TM)
Authors
Corda, Stephen (NASA Dryden Flight Research Center Edwards, CA, United States)
Vachon, Michael Jacob (NASA Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
September 7, 2013
Publication Date
February 1, 2006
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA/TM-2006-213673
H-2630
Funding Number(s)
WORK_UNIT: WU 24-723-54-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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