A preliminary low-speed wind-tunnel investigation of a thin delta wing equipped with a double and a single slotted flap

Report presenting a low-speed wind-tunnel investigation to determine the high-lift characteristics of a thin delta wing equipped with a single and double slotted trailing edge flap. Results regarding the lift, drag, and pitching-moment characteristics of the plain wing and various flap configurations are provided. The maximum lift coefficient of the model could be increased from 1.45 for the plain wing to 1.86 when the double slotted flap was deflected to 50 degrees.