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.