Aerodynamic Optimization of Wing by Camber Morphing using Cfd

This paper presents the CFD analysis of the 2-Dimensional NACA0012 airfoil carried out for identifying its aerodynamic coefficients (Lift and Drag coefficients), then further implementing morphing technology on the same two-dimensional NACA0012 airfoil, again carrying out CFD analysis to determine its aerodynamic coefficients (Lift coefficient (CL) and Drag coefficient (CD), then comparing the results of both the airfoil shapes particularly to the amount of Lift generated to prove that morphing airfoil produces more amount of Lift when compared to typical airfoil shapes. Using ANSYS Design modeler airfoil geometry was created and morphing shape could be achieved by XFLR5 software further the analysis is carried out using FLUENT 18.1 at subsonic flow. This morphing enables to improve aerodynamic efficiency.