Flow over an airfoil

Aim- Model the flow over a NACA0017 airfoil

Objective - 1.Model the flow over a NACA0017 airfoil

2. For the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces

Theory -

Geometry

Output results and plots

Attack - 0

Drag force

Lift Force

Attack - 2

Drag force

Lift Force

Attack - 4

Drag force

Lift Force

Attack - 6

Drag force

Lift Force

Attack - 8

Drag force

Lift Force

Attack - 10

Drag force

Lift Force

Explanation of results

1.The drag force and lift force becomes constant after some iterations which indicates that the solution has converged to a value and can be accepted.

2. Lift force increases with increase in angle of attack.

3. Drag force increases with increase in angle of attack.

4. Lift force is almost zero at 0 angle of attack.

5. Local mesh should be provided for better results.

Conclusion

Hence , the drag and lift values for all the angle of attacks are found out and the corresponding graphs are also plotted.