Multi element airfoils are high lift devices and provide improved aerodynamic characteristics which are beneficial for several applications such as aircraft wings, wind turbine blades. Simulations were performed using the computational panel code developed in MATLAB for the airfoils, 30P30N, GA (W)-1, RAF16, NLR 7301 configurations. The results were obtained for varying angle of attacks from -10 to 20 deg to include the effects of turbulence. The lift and drag coefficients are evaluated for the airfoil configurations, 30P30N, for Reynolds number range of 1.6x10~(5)-1x10~(6). The velocity and pressure contours distributions are illustrated to predict the laminar to turbulent flow characteristics on the airfoil surface. The maximum lift coefficient for single slotted flap element is found to decrease for large angle of attack beyond the stall region and for slat element the increase in lift is found to be marginal at high angle of attack. The maximum lift coefficient obtained including flap and slat elements is 3.62 and the drag coefficient is 0.368.
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