Experimental investigation of Gurney flaps on the lift enhancement of a delta wing

An experimental wind-tunnel investigation was undertaken to determine the effects of Gurney flaps on a 40° delta wing at a chord Reynolds number of 250,000. In the experiment, the height of the Gumey flaps was varied from 0.01 C to 0.05 C, and the sideslip angle of the model was selected as 0°, 5°, 10° and 20°. In comparison with the baseline clean configuration results, it was found that the model with plate Gurney flaps can indeed increase the lift-to-drag ratio at moderate to high lift coefficient for the wing, and the greatest increment was obtained for the 0.01 C Gurney flap. The effect of Gurney flap on the increment of lift-to-drag ratio trends to be not significant with the increase of sideslip angle.