Numerical Analysis of Flow Over NACA0012 at Fixed Mach Number using Computational Fluid Dynamics

In this present work, we carry out a numerical analysis of lift and drag performances of NACA0012 airfoil at various angles of attack, by using computational fluid dynamic software. We can also utilize wind tunnel testing setup, to determine lift and drag force. In this investigation process, the design model has to be placed in the test section. This process is more laborious and expensive, than computational fluid dynamic techniques. This analytical method can be experimental, by investigation test. This numerical analysis of the two dimensional subsonic flow over a NACA0012 a airfoil at various angle of attack ranging from 2 to 10 degree (at a difference of 2 degree) at fixed Mach number 0.44 is presented. For this analysis we use k-ω SST turbulence model. The final result of analysis of CFD simulation shows the similarity to the exiting finding in the modern literature. Through this research we are proposing a reliable alternative experimental method for determining co-efficiency of drag and lift.