Flow over an Airfoil

The Aim is to study the flow over an airfoil for the different angle of attack

The angle of attacks are -0,2,4,6,8,10 degree

The airfoil we are using in this project is NACA0017 airfoil

1)For AOA =0

2)For AOA =2

3)For AOA =4

4)For AOA =6

5)For AOA =8

6) For AOA =10