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Status of the Validation of High-Angle-Of-Attack Nose-Down Pitch Control Margin Design GuidelinesThis paper presents a summary of results obtained to date in an ongoing cooperative research program between NASA and the U.S. Navy to develop design criteria for high-angle-of-attack nose- down pitch control for combat aircraft. A fundamental design consideration for aircraft incorporating relaxed static stability in pitch is the level of stability which achieves a proper balance between high- speed performance considerations and low-speed requirements for maneuvering at high angles of attack. A comprehensive data base of piloted simulation results was generated for parametric variations of critical parameters affecting nose-down control capability. The results showed a strong correlation of pilot rating to the short-term pitch response for nose-down commands applied at high- angle-of-attack conditions. Using these data, candidate design guidelines and flight demonstration requirements were defined. Full- scale flight testing to validate the research methodology and proposed guidelines is in progress, some preliminary results of which are reviewed.
Document ID
20040121214
Acquisition Source
Langley Research Center
Document Type
Other
Authors
Ogburn, Marilyn E. (NASA Langley Research Center Hampton, VA, United States)
Foster, John V. (NASA Langley Research Center Hampton, VA, United States)
Pahle, Joseph W. (NASA Dryden Flight Research Center Edwards, CA, United States)
Wilson, R. Joe (NASA Dryden Flight Research Center Edwards, CA, United States)
Lackey, James B. (Naval Air Warfare Center Patuxent River, MD, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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