Numerical investigation and validation of joukowski airfoil

In aircraft, airfoil role is very important to create the require lift to carry the aircraft. Aerodynamic characteristic of an airfoil is based on design but it desired performance of an airfoil is based on design but is results is not so easy. In present time airfoil design is tested randomly for the flow of an aircraft and first time wright brothers design cambered airfoil and In early days NACA provides a proper definition of an airfoil and tell us their property anyhow they economical. In this study of NACA0012, NACA4412 and JOUKOWSKI (T=12%)airfoil, at various angle of attack and 43.822 m/s flow velocity in the ANSYS - fluent. The very important aim of this study is to know about fluid flow behavior situated on every side of an airfoil and determine the aerodynamics performance characteristic at high Reynolds Numbers (3 million) and AOA vary from 2 degree to 18 degree. The lift and drag coefficients for all airfoil is calculated by observing at measuring surface pressure on the various airfoil. In this work aerodynamic performance of an airfoil are plotted against AOA and how they are different from experimental results.