Abstract
Thin-airfoil theory is applied to the lift problem of an airfoil with a Gurney flap. The lift and pitching moment coefficient increments are given as a square-root function of the relative Gurney flap height, and they are proportionally related. This model interprets the Gurney flap lift enhancement as a special camber effect. The theoretical relations are in good agreement with experimental and numerical data for several different wings. The theoretical method developed in this paper can be applied to similar trailing-edge devices for lift enhancement, and it is useful in the preliminary design of these flow control devices.
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