Flow over an airfoil
Objective:
Model the flow over a NACA0017 airfoil for the angle of attacks 02,4,6,8,10 compare the lift and drag forces.
Theory:
Airfoil shape like that of an airplane wing, tail, or propeller blade produces lift and drag when moved through the air. An airfoil produces a lif5in force that acts normally to the airstream and a dragging force that acts in the same direction as the airstream.
Drag is a consequence of the production of lift/thrust and acts parallel to the airflow.
Procedure:
• From NACA airfoil website NACA 0017 XYZ data collected and curve drawn using Solidworks command.
• The curve is converted and sketching done.
• For various the angle of Attacks the entity is rotated.
• The airfoil hence formed is extruded.
• Flow simulation is initiated by creating a new wizard with an input velocity of 500m/s.
• Th computational domain extended as per the requirement.
• Mesh create and goal option is used to get drag and lift force.
• After running the simulation cut plot is created for XY plane
• Goal plot is created between drag and lift force.
Results:
1. When angle of attack = 0 degree
Velocity:
Pressure:
2. When angle of attack = 2 degree
Velocity:
Pressure:
3. When angle of attack = 4 degree
Velocity:
Pressure:
4. When angle of attack = 6 degree
Velocity:
Pressure:
5. When angle of attack = 8 degree
Velocity:
Pressure:
6. When angle of attack = 10 degree
Velocity:
Pressure:
| ANGLE OF ATTACK | LIFT FORCE | DRAG FORCE |
| 0 | 25.4 | 2433.80 |
| 2 | 1487.90 | 2500.76 |
| 4 | 2893.87 | 2637.85 |
| 6 | 4399.98 | 2850.67 |
| 8 | 5714.89 | 3159.33 |
| 10 | 7295.99 | 3564.70 |
Conclusions:
1. Lift force increases with an increase of angle of attack up to the critical angle after that it will decrease.
2. Increasing the angle of attack is also increases the drag force.
3. For a zero-degree angle of attack the lift force is very close to zero.