1. Create a new project and then a new part file.
2. Go to Insert-Curves-Curve through XYZ points.
3. Then browse the naca test data in txt file format.
4. goto sketch and use convert entities by selecting the curve and the line.
5. Then select move entities and rotate entities. Select the line and the spline and
give
an angle of attack of 2.
6. Extrude the sketch so that the aerofoil shape is obtained.
7. Save the file.
8. goto wizard tool in flow simulation and selct external flow with time dependent.
9. The working fluid to be selected is air.
10. Give X velocity of 600m/s.
11. Then edit computational domain and select XY plane. Further drag the domain so that
the outflow boundary is suffiently placed.
12. Right click on global goals and goto global goles. Select Force along X and Y and
also the Surface force along the same directions.
13. Then select surface goals and select thetop surface. In this surface integrate force
along X and Y axis.
14. Run the simulation.
15. Click on insert preview and select contours.
16. Goto goal plot and select surface plot.
17. Stop the simulation when you observe that there is no change in lift force.
18. Create a cut plot and select mesh and contours in which velocity is selected.
19. From the results we can observe that as that when the angle of attack is increasing,
the lift force will increase reducing th drag force.
20. The simulation results are attached below .