Aerodynamic Analysis on Double Wedge Airfoil at Different Mach Numbers with Varying Angle of Attacks Using Computational Fluid Dynamics

The aerodynamic analysis primarily focusses on choosing airfoil shapes to obtain better physical performance. Various shapes of the airfoil are being studied to attain a better and safer flight with the highest possible performance. On them, double wedge airfoils have different types of shocks at higher speeds. This paper aims to present the effects of change in the physical parameter for the Double wedge airfoil for the different range of Mach number with varying angle of attack. Thermodynamic parameters are studied for two different Double wedge airfoils with half wedge angle 5° and 10° respectively. Double wedge airfoil is analyzed at different angles of attack (AOA). The analysis is done using ANSYS fluent and the k c turbulence modeling method is carried out. Numerical simulated data was generated by using Tecplot. From the simulated result, the coefficient of Lift and Drag has been seen to decrease with the increase in Mach number and decrease in AOA. For same Mach number, increase in half wedge angle increases shock and expansion waves at 00 AONA. And pressure coefficient (Cp) increases in the first half region and decreases in the second half region of the wedge with the increase In half wedge angle.