Trailing edge flap influence on leading edge vortex flap aerodynamics

A study has been conducted to explore the effects of trailing edge flaps (TEF) on leading edge vortex flap (LEVF) aerodynamics. A variety of LEVF and TEF configurations were tested on flat plate delta wings with leading edge sweep angles of 60 and 75 deg. Results indicated that the well-established vortex flowfield of the 75deg wing was not substantially improved with the deflection of trailing edge flaps. Significant changes were seen to occur to the marginal vortices of the 60-deg wing. For the 60-deg wing with inverted constant chord LEVFs, the deflection of TEFs resulted in substantial increases in lift coefficient at low angles of attack without sacrificing other performance parameters. Also shown is the capability for eliminating the adverse longitudinal characteristics of constant chord LEVFs.