Effect of Variation of Chord and Span of Ailerons on Rolling and Yawing Moments in Level Flight (1929)
NASA Technical Reports Server (NTRS) · leaf 6
maximum lift coefficient of the Clark Y wing and 0.52 of the maximum lift coefficient of the U. S. A. 27 wing. (Reference 3.) Observations were made with the ailerons set at angles of 8° to 16° to the wing chord and at 4° intervals thereafter up to 44°. The aileron angles were set by means of metal… … Fig. 5 Fig. fi Indication of unsteady flow about the ailerons was noted early in the investigation in the case of aileron angles greater than 16°. The effect of this burbUng flow was so marked on the rolling moment balance that considerably heavier damping was necessary than was used for the yawing…
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