An investigation was made in the Langley high-speed 7- by 10-foot tunnel by means of the transonic-bump method to determine the gust-alleviation capabilities of spoilers and deflectors when mounted on a 35° swept semispan wing having NACA 65AOO6 airfoil sections. The Mach number range was from 0.40 to 1.15, and the angle-of-attack range was from -8° to or beyond the stall.nThe gust-alleviation capabilities (as indicated by the reduction in lift-curve slope) were almost constant (approximately a 20-percent reduction in lift-curve slope) throughout the Mach number range from O.40) to 1.15 for both the deflector and the spoiler-deflector combination. Increased drag resulted from the deflection of these controls and indicated that they would also be effective as aerodynamic brakes during slowdown to rough-air speed.
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