Computational Fluid Dynamics (CFD) Analysis of NACA 0012 Airfoil – Zhexuan Wang – 1st Edition

The flow over the airfoil is an external flow. It is a kind of flow that flows over the outside the body of an object, in our case ‘the airfoil.’ These fluid flow moves around the airfoil.

Due to these flow there are forces developed that are normal and parallel to the flow, and these forces are called drag force and lift force. Drag force is a mechanical force generated by the airfoil moving through the fluid. And the lift force is the force that helps the airfoil to gain altitude. In this project, we are considering low speed air flow over the NACA 0012 airfoil at an angle of 2o and 14o . For the Reynolds number of 2.88× 106 this flow was modeled as an inviscid and incompressible flow. Using the Computational Fluid Dynamics (CFD) software “ANSYS” NACA 0012 airfoil in wind tunnel were simulated for different attack angle and mesh elements. Pressure contour, velocity vector, stream line, coefficient of drag and lift of the fluid were obtained from this simulation. Different boundary conditions were needed to be setup in order to solve the continuity equation and Navier-Stokes equation for two dimensional flows