The effects of several spoiler arrangements on the spanwise variation of section twisting moments of a wing of NACA 230-series airfoil sections were investigated. The spoilers tested included both plain and perforated spoilers. The tests were conducted at a Reynolds number of 7,350,000 and a Mach number of 0.245;the tests included force and moment measurements and chordwise pressure-distribution measurements at six spanwise stations.nThe results of the tests indicated that the influence of a projected spoiler on the section pitching-moment coefficients extended approximately 25 percent of the semispan inboard of the spoiler. The maximum twisting-moment coefficients due to the spoilers at a low angle of attack of the wing were reached at this spanwise location.
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