Incremental pressure distributions due to the spoilers were in good agreement with previous flat-plate results and also with the results of tests of similar spoilers on a trapezoidal wing. The location of the spoiler apex determined the most forward influence of the spoilers on the pressures. The spanwise normal-force and pitching-moment loadings due to the spoilers were dependent on the relative location of the spoiler to the wing trailing edge, on spoiler sweep angle, on whether the spoiler was stepped, and on wing angle of attack. For all the spoiler configure tions that were tested exclusive of the half-span trailing-edge spoiler there was decreased stability in the high negative angle-of-attack range. Spoiler effectiveness in reducing wing lift and bending-moment coefficients generally was greatest for the full-span swept spoiler and least for the half-span unswept spoiler. The spoilers generally had little effect on the wing pitching moment except at the largest negative angles of attack and except for the trailing-edge spoiler.
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