Flow over an airfoil

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

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% (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.

For Angle of attack 0

For the angle of attack 2

For the angle of attack 4

For the angle of attack 6

For the angle of attack 8

For the angle of attack 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.

For a different angle of attack, the Lift and drag forces are calculated and are listed below.

These are the average values of SG forces in X(Drag force) and Y(Lift force) directions.