Analysis of flow over an aerofoil is done using icoFoam solver of openFoam. Results are validated with popular aerofoil results.

1. 2D flow past an airfoil with different angles of
attack
Submitted to Submitted by
- Dr Harish Dixit -Apurva Bhagat(me13m1026)
-Harshal Gijare (me13m1028)
-Rahul Devnagare(me13p1008)

2. Introduction to problem
●AIM:-To use CFD as a tool to illustrate the
concept of separation and how the airfoil angle of
attack affects the flow.
●Parameters Varied 1. Reynolds Number 2. Angle
of attack

3. Mesh Details
● ICEM-CFD is used to prepare a Mesh
● Quadrilateral cells are used because they can be streched
easily to account for different flow gradients in different
directions
● Mesh is more fine (High aspect ratio) near the airfoil surface.
● Parabola is choosen for far field boundary it has no
discontinuties in slope.
● .msh file is generated and imported to openFoam
● No of cells-9800.

4. Solver Details
● IcoFoam-Incompressible solver is used.
● Incompressible N-S equations are used for discretization
in this solver.
● Finite Volume Method is used for discretization.
● Euler scheme is used for time steping and Gauss linear
scheme is used for Pressure and velocity solution.
● Courant no < 0.5

5. Cases Studied.
● Kinematic Viscosity is fixed = 0.01
● Flow over aerofoil is observed at different angles of attack
1 degree to 15 degree at fixed reynolds number Re=500.
Flow seperation is observed.
● Reynolds number is varied by changing free stream
velocity. Re=100 to Re=20000

6. Velocity Contours at different angle of
attack (Re=500)
● Alpha = 1°
● Alpha = 7°
● Alpha = 15°● Alpha = 11°

7. Velocity contours at Re=500,angle of
attack = 1°

8. Velocity contours at Re=500,angle of attack = 3°

9. Velocity contours at Re=500,angle of
attack = 5°

10. Velocity contours at Re=500,angle of
attack = 7°

11. Velocity contours at Re=500,angle of
attack = 9°

12. Velocity contours at Re=500,angle of
attack = 11°

13. Velocity contours at Re=500,angle of
attack = 13°

14. Velocity contours at Re=500,angle of
attack = 15°

15. Pressure variation w.r.t angle of
attack
● Angle of attack = 3° ● Angle of attack = 7°
● Angle of attack = 15°● Angle of attack = 11°

16. Lift & Drag coefficients w.r.t. angle
of attack
● Typical Aerofoil Lift & Drag Curve ● Lift & Drag curve of Aerofoil under
study

17. Velocity contours at Re=100,angle of
attack = 5°

18. Velocity contours at Re=500,angle of
attack = 5°

19. Velocity contours at Re=1000,angle of
attack = 5°

20. Velocity contours at Re=5000,angle of
attack = 5°

21. Velocity contours at Re=10000,angle of
attack = 5°

22. Velocity contours at Re=20000,angle of
attack = 5°

23. Behaviour of flow w.r.t Reynolds no. (Velocity
contours)
● Re=100 ● Re = 500 ● Re =1000
● Re = 20000● Re = 10000● Re = 5000

24. Variation of coefficient of drag w.r.t. Re

25. Conclusion
● Reynolds number has no effect on the laminar separation point.
● Increasing Reynolds number can cause a transition to turbulent boundary layer
ahead of separation and effectively move the separation point downstream.
● Coefficient of lift increases as angle of attack increases (till stall angle) at fixed
Reynold no.
●Coefficient of drag increases as angle of attack increases (at fixed Re).
●Pressure drag dominates friction drag as angle of attack increases (at fixed
Re).
● Coefficient of drag decreases as Re increases (at fixed angle of attack)

26. Thank You!