Flow over an airfoil

Aim: You will be running simulations on NACA air foils

Objective:

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

INTRODUCTION:

In aerodynamics, angle of attack specifies the angle between the chord line of the wing of a fixed-wing aircraft and the vector representing the relative motion between the aircraft and the atmosphere. Since a wing can have twist, a chord line of the whole wing may not be definable, so an alternate reference line is simply defined.

Procedure:

1. Import the required air foil for the data base provided in the solidworks flow simulation module
2. Model the air foil as required and save it as new file.
3. Now open the new wizard and set the required boundary conditions like external flow, fluid, etc etc
4. Now define the outputs required in the global goals and surface goals.
5. After completion of simulation save the velocity, drag force and lift force plots.
6. Repeat the same procedure for different angles of attack and compare the results.

case 1: 0 degrees of attack

Velocity distribution

Drag force plot

Lift force plot

case 2: 2 degrees of attack

Velocity distribution

Drag force plot

Lift force plot

case 3: 4 degrees of attack

Velocity distribution

Drag force plot

Lift force plot

case 4: 6 degrees of attack

Velocity distribution

Drag force plot

Lift force plot

case 5: 8 degrees of attack

Velocity distribution

Drag force plot

Lift force plot

case 6: 10 degrees of attack

Velocity distribution

Drag force plot

Lift force plot

Conclusion:

1.Lift force increases with increase in angle of attack upto critical angle and then decreases.

2. Drag force also increases with increase in angle of attack.