Flow Analysis over an F-16 Aircraft Using Computational Fluid Dynamics

In the current era of globalization every prosperous nation in this world wishes to develop a fast moving aircraft with a high lift coefficient and low drag coefficient, which helps them to enhance their military force and strengthens its civilization’s foundation. The purpose of this study is to examine the viscous, incompressible and steady-state flow over the F-16 aircraft using computer modelling techniques and to compare the modelled results with the experimental results done with the help of wind tunnel. This paper outlines the development of a computational model of the F-16 model in modelling software and then the creation of 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 coefficient of pressure, lift coefficient, drag coefficient, etc. The aircraft being a military aircraft travels at speed of Mach 2, which is around 1,500 mph at an altitude of 50,000 ft. This paper will give the future generation to think in a manner to develop the aerospace field and the CFD field too. Keywords— ANSYS Fluent 14, ANSYS ICEM CFD 14, Drag Coefficient (CD), F-16 Aircraft, Lift Coefficient (CL), Mach number and Velocity.