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Characteristics of a Sealed Internally Balanced Aileron from Tests of a 1/4-Scale Partial-Span Model of the Republic XF-12 Airplane in the Langley 19-Foot Pressure TunnelThis paper presents the results of the aileron investigation and includes rolling-moment, yawing-moment, and aileron hinge-moment coefficients and pressure coefficients across the aileron-balance seal through a range of angle of attack, tab deflection, and aileron deflection with flaps neutral and deflected 20 degrees and 55 degrees. Some of the effects of wing roughness and balance seal leakage on the aileron and tab characteristics are also presented.
Document ID
20050019579
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Graham, Robert R. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Martina, Albert P. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Salmi, Reino J. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
November 1, 1946
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-L6I18
Report Number: NACA-RM-L6I18
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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