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Fixed-base simulator investigation of the effects of L [alpha] and true speed on pilot opinion of longitudinal flying qualities

Author: Charles R Chalk; Aeronautical Systems Division (U.S.).; Cornell Aeronautical Laboratory.
Publisher: Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Research and Technology Division, Air Force Systems Command, 1963.
Series: Technical documentary report (United States. Air Force. Systems Command. Aeronautical Systems Division)), ASD-TDR-63-399
Edition/Format:   Book : National government publication : English
Database:WorldCat
Summary:
The study is directed toward investigating the effects on pilots rating of large variations (L alpha) in the relative amplitude and phase of the basic airplane responses to elevator control. The effects of L alpha and true speed on longitudinal flying qualities, optimum control gain, and normal acceleration response to turbulence were investigated in a ground simulator. The steady state ratio of normal acceleration  Read more...
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Material Type: Government publication, National government publication
Document Type: Book
All Authors / Contributors: Charles R Chalk; Aeronautical Systems Division (U.S.).; Cornell Aeronautical Laboratory.
OCLC Number: 456272991
Notes: "November 1963."
AD0430012 (from http://www.dtic.mil).
Research supported by the United States Air Force, and performed by the Cornell Aeronautical Laboratory, Inc.
Description: xi, 164 p. : ill. ; 29 cm.
Series Title: Technical documentary report (United States. Air Force. Systems Command. Aeronautical Systems Division)), ASD-TDR-63-399
Responsibility: author, Charles R. Chalk.

Abstract:

The study is directed toward investigating the effects on pilots rating of large variations (L alpha) in the relative amplitude and phase of the basic airplane responses to elevator control. The effects of L alpha and true speed on longitudinal flying qualities, optimum control gain, and normal acceleration response to turbulence were investigated in a ground simulator. The steady state ratio of normal acceleration to angle of attack was found to be of significance both to the flying qualities of an airplane and to the optimum longitudinal control gain. Normal acceleration response to rough air was demonstrated to be primarily a function of L alpha and the short period frequency and damping ratio.

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