CFD Analysis of F-16 Falcon

Development of a fast-moving aircraft with high lift coefficient and low drag coefficient is an essential requirement for the current scenario to support to modernize the military capability of any independent Nation. In this context, the aim of our project is to examine the Viscous, Compressible and Steady-state flow over the F-16 Fighting Falcon aircraft using computer modeling techniques and to compare the modeled results with the analytical results to emphasize the modernization and warble capability. This project outlines the development of a computational model of the F-16 Fighting Falcon model in a finite computational domain, segmentation of this domain into discrete intervals, application of the boundary condition such as Mach number or velocity and then obtaining the plots and results for the coefficient of pressure, lift coefficient, drag coefficient, etc.