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Oblique-wing research airplane motion simulation with decoupling control lawsA large piloted vertical motion simulator was used to assess the performance of a preliminary decoupling control law for an early version of the F-8 oblique wing research demonstrator airplane. Evaluations were performed for five discrete flight conditions, ranging from low-altitude subsonic Mach numbers to moderate-altitude supersonic Mach numbers. Asymmetric sideforce as a function of angle of attack was found to be the primary cause of both the lateral acceleration noted in pitch and the tendency to roll into left turns and out of right turns. The flight control system was shown to be effective in generally decoupling the airplane and reducing the lateral acceleration in pitch maneuvers.
Document ID
Document Type
Conference Paper
Kempel, Robert W.
(PRC Kentron, Inc. McLean, VA, United States)
Mc Neill, Walter E.
(NASA Ames Research Center Moffett Field, CA, United States)
Maine, Trindel A.
(NASA Flight Research Center Edwards, CA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 88-0402
Accession Number
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