Flow over an airfoil
REMARKS
You did the challenge well. But we expect you to explain the results more in detail. So we are reducing some marks.
The objective is to simulate the flow over an airfoil for different angle of attacks & compare drag force & lift force for each angle of attacks.
- The airfoil used is NACA0018.
- Angle of attacks are 0,2,4,6,8,10
1. For Angle of Attack 0:-
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| Drag Force | [N] | 3286.371 | 3299.512 | 3275.659 | 3316.766 | 100 | Yes | 1.824112 | 80.9092 |
| Lift Force | [N] | -1.12128 | 6.317244 | -23.9505 | 44.62295 | 100 | Yes | 4.896537 | 2.492815 |
Pressure Distribution for aoa 0
Velocity Distribution for aoa 0
2. For Angle of Attack 2:-
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| Drag Force | [N] | 3344.851 | 3349.688 | 3334.951 | 3370.839 | 100 | Yes | 2.138 | 79.551 |
| Lift Force | [N] | 1412.293 | 1431.389 | 1396.74 | 1471.711 | 100 | Yes | 6.251 | 28.264 |
Pressure Distribution for aoa 2
Velocity Distribution for aoa 2
3. For Angle of Attack 4:-
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| Drag Force | [N] | 3464.634 | 3479.597 | 3458.613 | 3499.508 | 100 | Yes | 24.41269 | 83.10572 |
| Lift Force | [N] | 2841.503 | 2814.484 | 2755.455 | 2865.372 | 100 | Yes | 44.00535 | 51.51521 |
Pressure Distribution for aoa 4
Velocity Distribution for aoa 4
4. For Angle of Attack 6:-
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| Drag Force | [N] | 3713.524 | 3702.089 | 3675.247 | 3721.587 | 100 | Yes | 4.309542 | 85.35508 |
| Lift Force | [N] | 4347.18 | 4319.094 | 4279.668 | 4348.548 | 100 | Yes | 68.8794 | 78.25289 |
Pressure Distribution for aoa 6
Velocity Distribution for aoa 6
5. For Angle of Attack 8:-
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| Drag Force | [N] | 4005.415 | 4010.482 | 3995.032 | 4026.885 | 100 | Yes | 3.459469 | 93.33758 |
| Lift Force | [N] | 5817.398 | 5801.511 | 5784.122 | 5822.16 | 100 | Yes | 26.82007 | 102.4178 |
Pressure Distribution for aoa 8
Velocity Distribution for aoa 8
6. For Angle of Attack 10:-
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| Drag Force | [N] | 4399.4 | 4414.281 | 4386.895 | 4435.148 | 100 | Yes | 3.005275 | 102.0666 |
| Lift Force | [N] | 7220.753 | 7206.045 | 7183.092 | 7234.538 | 100 | Yes | 19.98759 | 125.9684 |
Pressure Distribution for aoa 10
Velocity Distribution for aoa 10
- Conclusion:-
In general, the greater the angle of attack, the more lift is generated by the wing. However, this is only true to a point. At some point the wing reaches its critical angle of attack, and at higher angles of attack the amount of lift generated drops dramatically. This is because the flow of air separates from the wing, forming turbulent eddies that destroy the ability of the wing to generate lift.Beyond the critical angle of attack is the stalled region, where the wing is no longer effectively generating lift and the airplane is stalled.
Drag Force vs AOA
Drag Force vs AOA
Here it is evident from the figure that as the angle of attack increases,Lift force & Drag force increases.