CFD Analysis On the Effect Of Circular Cavity at Different Location of Airfoil Surface

The paper presents the effect of cavity at different position of the airfoil on lift coefficient, drag coefficient and lift to drag ratio respectively. Here the analysis performed on SC (2) 0414 3D airfoil by using commercial CFD ANSYS FLUENT. The passive control method is applied by modifying the baseline airfoil surface coordinates to ascertain the aerodynamic behavior of the cavity at 40 %, 50% and 60 % of the chord length successfully where spalart turbulence model technique is chosen to solve boundary layer problems on adverse pressure gradient and tested at extended range of angle of attack -150 to 180. A structured meshing method was used. RANS, Reynolds averaged Navier-Stokes, was the solver used for the unsteady simulations. At Reynolds numbers (Re) of 10× 104 , the coefficients of lift, drag, pressure were observed. The study highlights the aerodynamic characteristics and stall effects at desired angle of attack. It is observed that the cavity at 40 % of the chord length offers improved performance at certain inclination whereas the cavity at mid chord shows remarkable lift and delay stall effect than the trailing edge cavity. Therefore, SC (2) 0414 airfoil with circular cavity at 50 % most suitable at high subsonic regime. Keywords: lift coefficient, drag coefficient and lift to drag ratio, airfoil