Flow over an airfoil

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.

For example, the NACA 2412 airfoil has a maximum camber of 2% located 40°k (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord.

The pressure and velocity variation around the foil for a 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.

Forces acting on the airfoil

1. Drag force-acts in the direction of the velocity.

2. Lift force- acts in the direction perpendicular to the direction of velocity in the upward direction.

3. Total aerodynamic force-it is the resultant of drag and lift force.