Simulation and Modelling of NACA0017 airfoil to calculate lift and drag force at different angle of attacks i.e; 0,2,4,6,8,10.

Presented study, aims to provide detailed information about Simulation and Modelling of NACA0017 airfoil to calculate lift and drag force at different angle of attacks. The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA". The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties.

Operational procedure for Modelling the NACA0017 AIRFOIL.

1. Open New part file in Solidworks to Model NACA airfoil 0017, change the unit system to MKS System.

2. Load NACA0017 airfoil data from the curve menu i.e; Curve through XYZ.

3. Select the front plane and convert entities to change the curve into an editable sketch.

4. Start new sketch and close the airfoil for modelling.

5. Use Move entities option to rotate the airfoil at a different angle of attacks for eg: for attack angle of 6 degrees select spline and curve and give the angle of rotation -6.00 degree respect to the origin .

6. In presented experimental work we aimed towards simulating airfoil at angle of attack 0;2;4;6;8;10

7. Extrude airfoil sketch to 0.10m.

Operational Procedure for flow simulation:

1. In flow simulation, Start New project and enter required data like if the simulation is external or Internal or Time-dependent, effect of gravity etc, Used fluid, Velocity etc.

Parameters Given in experimental work:

External Simulation

Time-dependent

Fluid : Air

Velocity: 600m/s in X direction.

2. Resize computational domain in a defined ratio like 5 times from left and 10 times to the right and enter parameters like type of simulation 2D or 3D and plane.

Therefore, selected Simulation is 2D in the X Y plane.

3. Enter Goals of simulation like global goals, surface goals, volume goals, equation goals.

Global Goals: Max Force X Y, Max Friction force X Y

Surface Goal at Front Face: Force X Y that is Lift and Drag force.

4. Provide Mesh details like type of mesh Global Mesh, Local Mesh.

Local Mesh at front face : 3

5. Run the solver for simulation to generate the report.

Results:

Simulation for the 0-degree angle of attack:

Velocity Cut plot :

Pressure cut plot:

Simulation for the 2-degree angle of attack.

Cutplot Pressure:

Cutplot Velocity:

Simulation for the 4-degree angle of attack.

Cutplot Pressure:

Cutplot Velocity:

Simulation for the 6-degree angle of attack.

Cutplot Velocity:

Cutplot Pressure:

Simulation for the 8-degree angle of attack.

Cutplot Pressure:

Cutplot Velocity:

Simulation for the 10-degree angle of attack.

Cutplot Velocity:

Cutplot Pressure:

Conclusion:

Above shown results provide information about. how change in the angle of attack there is a sudden increase change in lift and drag forces.