Performance Analysis on Effect of Cavity on Supercritical Airfoil SC (02)- 0414 Variable Thickness

This paper explores the numerical analysis on supercritical airfoil NACA SC (02)0414 tested at high subsonic regime to determine the optimized aerodynamic characteristics respectively. To better understand the airfoil performance, the passive flow control technique using circular cavity is introduced on the suction surface extensively. This research work presents simulation analysis on dynamically modified supercritical airfoil upper surfaces having circular cavities at leading edge. Inorder to explore the aerodynamic effects ANSYS FLUENT software widely used for compressible flow Mach number 0.8-0.9 respectively. Further, dynamic modification carried out on baseline airfoil with 15% reduction in its thickness. In the present study, simulation was executed in Ansys Fluent, using the SST K-ω turbulence model to predict the critical flow properties of the base profile and for suction surface of 15% reduced thickness at M = 0.89 for wide angle of attack ranges from -5° to 15° . Structured mesh employed. Lift, Drag, Velocity and Pressure contour observed at Reynolds number 2.1x10-6 to determine airfoil modifications. Thus the finding highlights improved performance for reduced airfoil upper surface with cavity placed at suction surface whereas baseline foil cavity at suction face performed least in terms of lift and drag coefficient. Thus the circular cavity offers feasible results up to at angle of attack 12.Therefore, from the simulated results, when the thickness is reduced to 15% with a cavity on the surface, the lift, drag and L/D ratio shows a remarkable effect than base airfoil with a cavity and thus enhanced aerodynamic performance of airfoil. Keywords:- Supercritical Airfoil, Lift, Drag, Angle of attack, Passive flow control technique