An engineering method for the determination of aeroelastic effects upon the rolling effectiveness of ailerons on swept wings Page: 3 of 83
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2 NACA RM L53H114
In recent years, many methods have been proposed to account for the
effects of aeroelasticity upon the lateral-control characteristics of
swept wings. Because of the complicated interaction of structural and
aerodynamic effects, the theories which have been developed are neces-
sarily complex. Relatively simple methods for making such estimates for
unswept wings at both subsonic and supersonic speeds are available; how-
ever, a comparable method for swept wings which does not involve the use
of difficult mathematical procedures and which is relatively rapid and
reasonably accurate has not been available. Such a method would be of
particular importance in preliminary design.
In order to correlate the test results of the more than 370 suc-
cessful lateral-control test models which have been flown by the Langley
Pilotless Aircraft Research Division in the course of a general investi-
gation of lateral control over a speed range which extended from approxi-
mately M = 0.6 to as high as M = 1.8, it was necessary to account for
the effects of aeroelastic distortion. Because of the great number and
variety of wing-control configurations, the application of a highly
refined aeroelastic theory would have been exceedingly tedious. The
purpose of this paper is to present the engineering method which was
derived and the comparison of the values calculated by this method with
The results of this investigation for ailerons are presented in non-
dimensional form and have been calculated for a range of tapered wings
varying from 0 to 1.0 in taper ratio, for wing-span--body-diameter ratios
of 0, 0.2, and 0.4 and for ailerons of any spanwise extent and location.
An example problem is outlined in appendix A. In addition, some
experimentally determined structural constants are compared with those
calculated by approximate methods. This comparison is given in appendix B.
AR aspect ratio, b2/S
A dimensionless angle of twist resulting from the component of
the aerodynamic moment parallel to the direction of flight
caused by unit control deflection,
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Strass, H. Kurt & Stephens, Emily W. An engineering method for the determination of aeroelastic effects upon the rolling effectiveness of ailerons on swept wings, report, November 30, 1953; (digital.library.unt.edu/ark:/67531/metadc59770/m1/3/: accessed October 21, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.