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Flight and wind-tunnel calibrations of a flush airdata sensor at high angles of attack and sideslip and at supersonic Mach numbersA nonintrusive airdata-sensing system was calibrated in flight and wind-tunnel experiments to an angle of attack of 70 deg and to angles of sideslip of +/- 15 deg. Flight-calibration data have also been obtained to Mach 1.2. The sensor, known as the flush airdata sensor, was installed on the nosecap of an F-18 aircraft for flight tests and on a full-scale F-18 forebody for wind-tunnel tests. Flight tests occurred at the NASA Dryden Flight Research Facility, Edwards, California, using the F-18 High Alpha Research Vehicle. Wind-tunnel tests were conducted in the 30- by 60-ft wind tunnel at the NASA LaRC, Hampton, Virginia. The sensor consisted of 23 flush-mounted pressure ports arranged in concentric circles and located within 1.75 in. of the tip of the nosecap. An overdetermined mathematical model was used to relate the pressure measurements to the local airdata quantities. The mathematical model was based on potential flow over a sphere and was empirically adjusted based on flight and wind-tunnel data. For quasi-steady maneuvering, the mathematical model worked well throughout the subsonic, transonic, and low supersonic flight regimes. The model also worked well throughout the angle-of-attack and sideslip regions studied.
Document ID
19930046934
Document Type
Conference Paper
Authors
Moes, Timothy R. (NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Whitmore, Stephen A. (NASA Flight Research Center Edwards, CA, United States)
Jordan, Frank L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Subject Category
AIRCRAFT INSTRUMENTATION
Report/Patent Number
AIAA PAPER 93-1017
Meeting Information
AIAA, AHS, and ASEE, Aerospace Design Conference(Irvine, CA)
Distribution Limits
Public
Copyright
Other