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Pitch control margin at high angle of attack - Quantitative requirements (flight test correlation with simulation predictions)Recent mishaps and incidents on Class IV aircraft have shown a need for establishing quantitative longitudinal high angle of attack (AOA) pitch control margin design guidelines for future aircraft. NASA Langley Research Center has conducted a series of simulation tests to define these design guidelines. Flight test results have confirmed the simulation studies in that pilot rating of high AOA nose-down recoveries were based on the short-term response interval in the forms of pitch acceleration and rate.
Document ID
19930027280
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lackey, J.
(NASA Langley Research Center Hampton, VA, United States)
Hadfield, C.
(U.S. Navy, Naval Warfare Center Patuxent River, MD, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: AIAA Biennial Flight Test Conference, 6th, Hilton Head Island, SC, Aug. 24-26, 1992, Technical Papers (A93-11251 01-05)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-4107
Accession Number
93A11277
Distribution Limits
Public
Copyright
Other

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