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Flight test of the X-29A at high angle of attack: Flight dynamics and controlsThe NASA Dryden Flight Research Center has flight tested two X-29A aircraft at low and high angles of attack. The high-angle-of-attack tests evaluate the feasibility of integrated X-29A technologies. More specific objectives focus on evaluating the high-angle-of-attack flying qualities, defining multiaxis controllability limits, and determining the maximum pitch-pointing capability. A pilot-selectable gain system allows examination of tradeoffs in airplane stability and maneuverability. Basic fighter maneuvers provide qualitative evaluation. Bank angle captures permit qualitative data analysis. This paper discusses the design goals and approach for high-angle-of-attack control laws and provides results from the envelope expansion and handling qualities testing at intermediate angles of attack. Comparisons of the flight test results to the predictions are made where appropriate. The pitch rate command structure of the longitudinal control system is shown to be a valid design for high-angle-of-attack control laws. Flight test results show that wing rock amplitude was overpredicted and aileron and rudder effectiveness were underpredicted. Flight tests show the X-29A airplane to be a good aircraft up to 40 deg angle of attack.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Bauer, Jeffrey E.
(NASA Flight Research Center Edwards, CA, United States)
Clarke, Robert
(NASA Flight Research Center Edwards, CA, United States)
Burken, John J.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1995
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.60:3537
Accession Number
Funding Number(s)
PROJECT: RTOP 505-64-30
Distribution Limits
Work of the US Gov. Public Use Permitted.
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