Investigation of variation in the leading edge shapes on the aerodynamic characteristics over a delta wing

The present study deals with the effect of varying the slender delta wing's leading edge shapes on the aerodynamic characteristics using a subsonic wind tunnel. A force balance system computed the surface pressure measurement for three leading-edge shapes. The leading edges for the present study are sharp, circular and hybrid. The angle of attack is varied from 0o to 35o and has a freestream velocity of 15m/s. The lift and drag coefficients were computed and compared for all the leading edge shapes of the delta wing. The comparative analysis depicts the highest aerodynamic efficiency for the delta wing with a circular leading edge. Based on the results obtained from the surface pressure distribution, the circular leading edge possesses the highest vortex strength and further delays the flow separation, thereby increasing the operating range of the angle of attack.