CFD - Flow over a NACA0017 airfoil

NACA Airfoil

Objective

Model the flow of air over a NACA0017 airfoil for the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces along the ordinate and abscissae

Procedure

• NACA0017 co-ordinates were chosen from the airfoil database and the curve is generated in solid works Following which the foil is extruded to the desired length
• An External flow is chosen and the medium is chosen as air and speed of air is given at X direction as 600 m/s
• Global Goals are set in the X and Y direction and Local Goals are set on the surface of the airfoil to increase the detail of mesh. The surface goal force along Y direction will give the lift force while the surface goal force along X gives the drag force.
• Global mesh settings are set to a higher refinement number and flow simulation is run for various angle of attacks.
• Various angle of attack ranging from 0,2,4,6,8,10 are studied.

Velocity plot of NACA007 at 0 degree angle of attack

Velocity plot of NACA007 at 2 degree angle of attack

Velocity plot of NACA007 at 4 degree angle of attack

Velocity plot of NACA007 at 6 degree angle of attack

Velocity plot of NACA007 at 8 degree angle of attack

Velocity plot of NACA007 at 10 degree angle of attack

Conclusion

After the simulation at various angle of attacks it is found that the while the drag force may vary from the range 0.008 - 0.011 the lift force is extremely low for 0 angle of attack and as the angle of attack is increased we see the lift force increasing from -0.000005 to 0.016 and hence it can be concluded that the best angle of attack in the case of a NACA0017 Airfoil is 10 Degrees.