Flow simulation over an NACA-0017 aerofoil with different angle of attacks using SolidWorks (Computational Fluid Dynamics)

Aim:

To perfrm a flow simulation analysis over an NACA 0017 aerofoil for different angles of attack, also analyse the drag force and lift force for different angles of attack.

Objective:

1. Model the NACA 0017 aerofoil shape using data exported from Aerofoil database.
2. Setup an external flow simulation analysis with a velocity of 600m/s in x direction.
3. provide the required global and surface goals to be found.
4. Analyse the results for various angles of attack.

System parameters:

fluid: Air

Velocity of fluid: 600 m/s

Computational domain parameters:

In front of the aerofoil, 5 times the chord length. Behind aerofoil, 20 times the chord length. Above and below 10 times the chord length.

Simulation time: 5 sec.

Lift force = Force along Y direction

Drag force = Force along X direction

Results:

Baseline configuration

Angle of attack: 0 deg

Force along X direction:

Summary:

Pressure plot:

Velocity plot

Case 1:

Angle of attack: 2 deg

Force along X direction

Force along Y direction:

Summary:

Pressure plot:

Velocity plot:

Case 2:

Angle of attack: 4 deg

Force along X direction:

Force along Y direction:

Summary:

Pressure plot:

Velocity plot:

Case 3:

Angle of attack: 6 deg

Force along X direction:

Force alonge Y direction:

Summary:

Pressure plot

Velocity plot

Case 4:

Angle of attack: 8 deg

Force along X direction:

Force along Y direction:

Summary:

Pressure plot:

Velocity plot:

Case 5:

Angle of attack: 10 deg

Force along X direction:

Force along Y direction:

Summary:

Pressure plot:

Velocity plot:

Conclusion:

Hence, from the above results and plots it is evident that increasing the angle of attack there is considerable increase in the thrust force generated. also, it is seen that the drag force increases as the angle of attack is increased.