Abstract

The work in this paper deals with reconstructing and optimizing the wing geometry of an Unmanned Combat Aerial Vehicle for improved performance and reviewing the impact of the modification on flight parameters in a steady flight The behavior of airfoils at planned flight conditions under I S A is checked in XFLR5 software Following up by 2-D CFD and boundary layer analysis of former and new airfoil dimensions of the wing are re-developed keeping the fuselage and tail structure same The existing wing and the optimized wing design is analyzed by Vortex Lattice Method and Triangular Panel Method with an objective to make the shape of the wing aerodynamically suitable for an increased Lift to Drag ratio and thereby minimizing drag coefficients