Flow over an airfoil

AIM: Deriving Relationships between Drag force and lift force along different angle of attacks of an Airfoil(NACA0017)

OBJECTIVE:

1.Designing airfoil using sample airfoil data

2. Performing CFD on an airfoil at a different angle of attack and plotting the relationships between drag force and lift force.

3.Making cut plots of Velocity and pressure of airfoil at a different angle of attacks

THEORY:

Airfoil:

This NACA airfoil series is controlled by 4 digits e.g. NACA 2412, which designate the camber, position of the maximum camber and thickness.

PROCEDURE:

1.1st insert the curve through x,y,z points by browsing the data from NACA tech data.

2. Sketch the airfoil through convert entities and using the move component to set the angle of the airfoil.

3. Extrude and make a solid body.

4.Switch to Solidworks add on and go to flow simulation and make wizard with proper requirements

5. Flow is external and transient with the velocity of air in the x-direction.

6. The computational domain is created, now change it to 2D and arrange the domain with 15D to forward of the airfoil and 5D to behind the airfoil similarly 15D to both top and bottom of the airfoil where D is the chord length.

7. Make Goal simulation of Integrated force along X and Y.

8. Basic mesh along with local mesh at the face of the airfoil.

9. Run the simulation

10. Save the data of drag and lift force at a different angle of attack and save the cut plots of velocity and pressure along with its animation.

Observations:

1. Drag force and lift force are increasing rapidly with increase in the angle of attack since because of more surface are in contact with the airflow.

2. Velocity contour at upper side of the airfoil increases logarithmically as there is increase in the angle of contact.