Wind Tunnel Tests of 16 Percent Thick Airfoil Section with Spoilers at Different Chordwise Positions

摘要

Wind tunnel tests were carried out at low speeds on a 16 percent thick, moderately cambered airfoil section equipped with spoilers at 7 different chordwise positions on the forward half part of the airfoil. Two spoiler positions were on the pressure side, two at the leading edge, and three on the suction side of the airfoil. The effect of spoiler height was examined. The spoiler height varied between 2.5 to 12.5 percent of the airfoil chord. The results indicate that a spoiler on the airfoil suction side positioned 5 percent of the chord from the leading edge is capable of eliminating the strong driving tangential force of the basic airfoil for the entire range of positive angles of attack tested.