Design and Flight Evaluation of a New Force-Based Flow Angle Probe

Corda, Stephen and Vachon, Michael Jacob (2006) Design and Flight Evaluation of a New Force-Based Flow Angle Probe. Technical Report NASA/TM-2006-213673, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

A 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.

EPrint Type:	NASA Technical Memorandum
Keywords:	Aerodynamics, Airdata probes, Angle-of-attack probes, F-15B Flight testing, Flow angle measurement
Subjects:	Aircraft/Project: F-15B (01 - 09) Aeronautics: (07) Aircraft Propulsion And Power (01 - 09) Aeronautics: (05) Aircraft Design, Testing And Performance (01 - 09) Aeronautics: (02) Aerodynamics
ID Code:	767
Deposited On:	28 Febuary 2006
Additional Information:	39 pages. Corda, Vachon, NASA Dryden Flight Research Center.