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Preliminary results from a subsonic high-angle-of-attack flush airdata sensing (HI-FADS) system - Design, calibration, algorithm development, and flight test evaluationA nonintrusive high angle-of-attack flush airdata sensing (HI-FADS) system was installed and flight-tested on the F-18 high alpha research vehicle. This paper discusses the airdata algorithm development and composite results expressed as airdata parameter estimates and describes the HI-FADS system hardware, calibration techniques, and algorithm development. An independent empirical verification was performed over a large portion of the subsonic flight envelope. Test points were obtained for Mach numbers from 0.15 to 0.94 and angles of attack from -8.0 to 55.0 deg. Angles of sideslip ranged from -15.0 to 15.0 deg, and test altitudes ranged from 18,000 to 40,000 ft. The HI-FADS system gave excellent results over the entire subsonic Mach number range up to 55 deg angle of attack. The internal pneumatic frequency response of the system is accurate to beyond 10 Hz.
Document ID
19900032691
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Whitmore, Stephen A.
(NASA Hugh L. Dryden Flight Research Facility Edwards, CA, United States)
Moes, Timothy R.
(NASA Flight Research Center Edwards, CA, United States)
Larson, Terry J.
(Analytical Mechanics Associates Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Instrumentation
Report/Patent Number
AIAA PAPER 90-0232
Accession Number
90A19746
Distribution Limits
Public
Copyright
Other

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