Effect of Variation of Chord and Span of Ailerons on Rolling and Yawing Moments at Several Angles of Pitch (1931)
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isplacement. British tests (Reference 2), in which a beyond 24° has little effect on the rolling moment at biplane cell was used, show the same tendency but to an angle of pitch of 8° for the Clark Y section. Figure a lesser degree. Figure 47 shows that the loss in rolling 26 shows that the limit… … same figures as the rolling moment coefficients. Thus -Vowing " " C// Figures 5, 15, 25, and 35 show the yawing moments -.06 produced by upward displacements. Figures 6, 16, 26, FicruK 47.—Clark Y wing section. Cl and Cs versus aileron angle for various and 36 by downward displacements for the…
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