Project

Flow over airfoil (NACA0012)

Problem statement : Determine drag coefficient , lift coefficient ,coefficient of pressure(Cp) at angle of attack of 4 degrees .

Mesh :

Nodes :26371

Elements : 25993

Results :

1. Pressure contours

2. Velocity contours

3. Turbulent kinetic energy :

4. Velocity streamlines

5. Velocity vectors

Ship work like this
in your own course.