Simulation of Flow over an airfoil Using SolidWorks

Aim:

To perform a flow simulation over a NACA 0017 airfoil using SolidWorks.

Objective:

1. To perform flow simulation over a NACA 0017 airfoil.
2. Then to compare the lift and drag forces at different values of angle of attack(0,2,4,6,8 and 10).

Theory:

1.NACA 0017 Airfoil

An airfoil-shaped body moving through a fluid produces an aerodynamic force. An airfoil or aero foil is the cross-sectional shape of a wing, blade (of a propeller, rotor, or turbine), or sail (as seen in cross-section).

The NACA airfoils are developed by the America's National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described by 4 digits following "NACA" e.g. NACA 0017, which designate the camber, position of the maximum camber and thickness. If an airfoil number is NACA MPXX then,

• M is the maximum camber divided by 100. In the example M=2 so the camber is 0.02 or 2% of the chord
• P is the position of the maximum camber divided by 10. In the example P=4 so the maximum camber is at 0.4 or 40% of the chord.
• XX is the thickness divided by 100. In the example XX=12 so the thickness is 0.12 or 12% of the chord.

2.Angle of attack

The angle between the line of chord of the airfoil and the relative airflow.

Software Used:

SolidWorks

Procedure:

The airfoil sketch is created and extruded as per the NACA0017 Airfoil file data as shown below,

The purpose of this project is to perform flow analysis over a NACA 0017 airfoil having air as a working fluid flowing externally over the airfoil. The flow simulation is performed in total six cases for different angles of attack, 0, 2, 4, 6, 8, 10.

1. The Analysis type is chosen as External.
2. And then Time-Dependent is selected and Simulation Time is set to 5 seconds with a Time Step of 1 second.
3. Working fluid is chosen as Air.
4. Type of flow is left as default.
5. The initial Velocity at x-direction is set to 600 m/s.
6. And the remaining things are left as default.
7. Velocity and pressure contours are obtained using cut plots for each cases.
8. Subsequently, the lift and drag forces are calculated for each case using Goals.
9. For all the angles of attack, lift and drag forces are compared.
10. And a conclusion is made from the analysis of the result.

Outputs:

1.Case(1) When Angle of attack is 0 °

1.1.Velocity Plot:

1.2.Pressure Plot:

1.3.Goal Plots for Drag and Lift Forces:

2.Case(2) When Angle of attack is 2 °

2.1.Velocity Plot:

2.2.Pressure Plot:

2.3.Goal Plots for Drag and Lift Forces:

3.Case(3) When Angle of attack is 4 °

3.1.Velocity Plot:

3.2.Pressure Plot:

3.3.Goal Plots for Drag and Lift Forces:

4.Case(4) When Angle of attack is 6 °

4.1.Velocity Plot:

4.2.Pressure Plot:

4.3.Goal Plots for Drag and Lift Forces:

5.Case(5) When Angle of attack is 8 °

5.1.Velocity Plot:

5.2.Pressure Plot:

5.3.Goal Plots for Drag and Lift Forces:

6.Case(6) When Angle of attack is 10 °

6.1.Velocity Plot:

6.2.Pressure Plot:

6.3.Goal Plots for Drag and Lift Forces:

References:

1. http://www.airfoiltools.com/
2. https://en.wikipedia.org/wiki/Airfoil

Conclusion:

As the angle of attack increases, the lift & drag forces also increases but as the angle of attack reaches a critical value called stall angle, then the lift force starts to reduce.