Theoretical and Computational Investigation on Swept Back Wing using CFD Method

Abstract

The principles of flight deals with the motion of air and forces acting on an aircraft. The theoretical aspects of aircraft deals with four different forces. The main aim of the study was to analyse the Swept Back Wing for Supersonic and Hypersonic Mach Regimes at various angles of attack. The geometry and analysis were done using Ansys-Fluent. Calculations were done for constant air velocity altering only the angle of attack. The findings present up the contours of pressure and velocity along with evaluation of lift, drag and its coefficients