Optimization on a 3-D wing for aerodynamic lift using NACA 2412 airfoil

The purpose of this project is to develop a procedure to numerically model airflow over wing using hypermesh and FLUENT. Three dimensional models for the airfoil 2412 were created, drawn and meshed in hypermesh using geometry data gathered by the National Advisory Committee for Aeronautics. Those models were read into FLUENT where boundary conditions flows were applied and the discretized Navier-Stokes equations were solved numerically. Numerical prediction of incompressible turbulent flow has been performed on a 3-D wing moving with a velocity of 50 m/s. CATIA, 3D modeling software was used to model 3D surface modeling of the wing. FLUENT, the computational fluid dynamics code, which in-corporate k-ε turbulence model and segregated implicit solver was used to perform computation. The aerodynamic analysis was performed to study the flow behavior of the air over the wing. The analysis includes the contours of pressure and velocity that impacts the wing followed by an evaluation of the coefficient of lift.