Aerodynamics Analysis of F-16 Aircraft

Abstract

The Lockheed Martin F-16 Fighting Falcon is the world’s most prolific fighter with more than 2000 in service. The primary objective of this research project is to evaluate the aerodynamics behaviour of the F-16 aircraft by conducting Computational Fluid Dynamics (CFD) analysis. The CFD simulations have been done in both subsonic and supersonic flight regimes. As a means of validating the results, the CFD analysis has been done with two different turbulence models. A 1:1 CATIA solid model of F-16 aircraft was used to generate computational mesh and subsequent CFD simulations were performed mainly with Fluent ANSYS. During the post processing phase of the CFD results, the aerodynamic characteristics of the F-16 have been predicted in terms of lift coefficient and drag coefficient over angles of attack ranges from 0° to 40°. In comparing CFD predictions between turbulence models, a minimal variation of those dimensionless quantities was recorded. At Mach number 0.6, formation of two large leading edge vortices which is the subsonic lift generation mechanism, were observed on the main wings. A complete analysis of shock waves and expansion fans formation around the aircraft was also performed at supersonic speed, by examining the static pressure variation. Further to examine flow over main wings, the surface static pressure variation and pressure coefficient variation at different span-wise locations have been also studied. The flow physics revealed with CFD analysis are well aligned with both subsonic and supersonic theories. The forecasted values for aerodynamic efficacy and dimensionless parameters are lower than expected. It has been found this particular fact is directly related to computational limitations associated with CFD. The outcomes from this piece of research not only provides better sight to fine details about fluid dynamics in relation to F-16, but also made vital recommendations for future CFD analysis of F16 aircraft.