Forward Facing Flap for Delta Wing Performance Improvement

Abstract

In the present study, the concept of forward facing flap mounted on a slender delta wing, originally proposed by Hurley is considered. The test model resulted in surfaces that deflected from the basic delta to form a simple X-configuration. With this configuration, force balance measurements were conducted at low speed in a low speed open circuit wind tunnel. The lift produced was found to be dependent on both the flap deflection angle and thickness. Overall, the results obtained are very promising as they show definitive trends in the lift performance improvement of the X-configuration over conventional base delta wing at low angles of attack.