Investigation of rolling and yawing moments due to ailerons of various chords and spans on two airfoils having Clark Y and U. S. A. 27 wing sections, in 10-ft. wind tunnel of Bureau of Standards on wing models of 60-in. span and 10-in. chord; measurements were made at various angles of pitch but at zero angle of roll and yaw, wing chord being set at angle of plus 4 deg. to fuselage axis.
Effect of variation of chord and span of ailerons on rolling and yawing moments at several angles of pitch
Nat. Advisory Committee Aeronautics -- Report
1931
27 pages
47 Figs.
Report
Englisch
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