Project on NACA Airfoil external flow in solidworks

Modeling of flow over a NACA0017 air foil and to compare the lift and drag forces on the foil for angle of attacks 0,2,4,6,8,10.

The pressure variation around the foil for different angle of attack is shown in the figure below

Parametrs

• Velocity in X direction- 600 m/s
• Surface roughness- 0
• Gravity -not considered
• Angle of attack-0,2,4,6,8,10

For angle of attack 0 degree

For angle of attack 2 degree

For angle of attack 4 degree

For angle of attack 6 degree

For angle of attack 8 degree

For angle of attack 10 degree

For different angle of attack the corresponding drag and lift force values are shown in the table below