Wind-tunnel research comparing lateral control devices, particularly at high angles of attack V : spoilers and ailerons on rectangular wings (1933)
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e of attack i for the various spoiler deflections in Figure 4. In addi- 030 tion, one run was made with an angle of yaw of 20° 8' and a spoiler deflection of 60°, the latter being the f assumed maximum deflection based on an examination 020 of the results, all of which are given in Table I.… … 16' 24' 32' 40' 8° the position along the chord is of interest mainly from Angle of of lock, ol the consideration of adverse rolling moments with low Piquee 4.—Boiling and yawing moment coefficients due to spoiler A deflections, the tests were made with the spoiler sense, it was thought desirable…
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