Numerical Observation Of Aerodynamic Characteristics Of A Biconvex Airfoil At Supersonic Flow

This study focuses on the observation of aerodynamic characteristics of a biconvex airfoil at high Mach number flow or supersonic flow. To understand the influence of supersonic flow on the aerodynamic characteristics of a biconvex airfoil numerical simulation was done using ANSYS Fluent. For the simulation purpose a twodimensional, turbulent, steady flow is considered. The simulation was done with appropriate flow domain and boundary conditions. A C-type flow domain is considered. SST k-ω viscous model is used to predict the flow turbulence. The simulation was done for Mach number 1.7. With the help of existing literature validation was done. Mesh independency test was also done. Flow visualization is done to view the shock waves and expansion waves clearly and properly. The outcomes reveal that with the increase of angle of attack the airfoil’s coefficient of lift increases until stall occurred. The stall occurred at an angle of attack 30° with a drastic loss of lift coefficient. The coefficient of drag also increases with the increase of angle of attack. The lift to drag ratio increases until 6° angle of attack than it falls. The biconvex airfoil shows maximum aerodynamic efficiency at 6° angle of attack