Flow Simulation on a NACA0017 airfoil at 600m s air speed
AIM: To model the flow over a NACA0017 airfoil for various angle of attacks and compare the lift and drag forces
INPUT PARAMETERS: Fluid - Air at 600m/s
PROCEDURE:
1) The airfoil is created as a part and extruded upto 200mm.
2) The flow simulation is a 2D simulation and computational domain is set
3) The global goals and surface goals are set
4) The local mesh is set along the airfoil surface
5) The simulation is run for around 1000 iterations till the values are constant (straight line graph). Then the calculation is stopped and the pressure profile and the goal plots are obtained.
6) Using cut plots, the velocity profile is obtained.
7) Using goal plots and Excel, the drag and lift forces are compared with the different angles of attack.
RESULTS:
For angle of attack = 0 degrees
VELOCITY PLOT
PRESSURE PLOT
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| SG Force (X) 1 | [N] | 0.478 | 0.482 | 0.478 | 0.485 | 100 | Yes | 0.004 | 0.074 |
| SG Force (Y) 1 | [N] | 0.006 | 0.006 | 0.004 | 0.008 | 100 | Yes | 3.01E-04 | 5.13E-04 |
For angle of attack = 2 degrees
VELOCITY PLOT
PRESSURE PLOT
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| SG Force (X) 1 | [N] | 0.48 | 0.483 | 0.48 | 0.486 | 100 | Yes | 0.005 | 0.071 |
| SG Force (Y) 1 | [N] | 0.782 | 0.778 | 0.773 | 0.782 | 100 | Yes | 0.009 | 0.01 |
For angle of attack = 4 degrees
VELOCITY PLOT
PRESSURE PLOT
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| SG Force (X) 1 | [N] | 0.558 | 0.559 | 0.558 | 0.561 | 100 | Yes | 0.003 | 0.059 |
| SG Force (Y) 1 | [N] | 1.581 | 1.576 | 1.568 | 1.581 | 100 | Yes | 0.013 | 0.02 |
For angle of attack = 6 degrees
VELOCITY PLOT
PRESSURE PLOT
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| SG Force (X) 1 | [N] | 0.696 | 0.697 | 0.696 | 0.698 | 100 | Yes | 0.002 | 0.04 |
| SG Force (Y) 1 | [N] | 2.359 | 2.358 | 2.356 | 2.359 | 100 | Yes | 0.004 |
0.031 |
For angle of attack = 8 degrees
VELOCITY PLOT
PRESSURE PLOT
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| SG Force (X) 1 | [N] | 0.901 | 0.9 | 0.899 | 0.901 | 100 | Yes | 5.04E-04 | 0.02 |
| SG Force (Y) 1 | [N] | 3.149 | 3.141 | 3.129 | 3.149 | 100 | Yes | 0.02 |
0.046 |
For angle of attack = 10 Degrees
VELOCITY PLOT
PRESSURE PLOT
| Goal Name | Unit | Value | Averaged Value | Minimum Value | Maximum Value | Progress [%] | Use In Convergence | Delta | Criteria |
| SG Force (X) 1 | [N] | 1.145 | 1.146 | 1.144 | 1.147 | 100 | Yes | 0.003 | 0.019 |
| SG Force (Y) 1 | [N] | 3.938 | 3.927 | 3.909 | 3.938 | 100 | Yes | 0.029 |
0.061 |
CONCLUSION:
Thus the velocity and pressure plots were obtained for 0,2,4,6,8 and 10 degree angles of attack and the drag anf lift forces were obtained in the form of tabulation.
From the graph plotted we can see that with increase in angle of attack, the lift and the drag force increases. But in the case of lift force, the level of increase is much higher. Since the angle of attack is only till 10 degrees, the stall angle is not reached. At this point, the lift decreases with increase in angle of attack.
Thus we can say, it is safe to increase the angle of attack beyond 10 degrees for now.