Week 7 - Minor Project
Week 7 - Minor Project
In this project, the student will have to setup the domain for analysis of flow over an airfoil at subsonic and supersonic regime. The airfoil will be analysed at 3 different angles of attack and the lift and drag coefficient will be compared in all cases
- Create domain for flow analysis
- Setup simulation for subsonic and supersonic regimes at
○5, 10, 15 angle of attack
In this Challenge, we are going to simulate the flow around a NACA0012 Airfoil in 3 different angles and airspeeds.
The angles are 5, 10 and 15 degree AOA.
NACA 0012 Airfoil Cordinates
Polyline = true
1 1 0.00126
1 0.992704 0.002274
1 0.979641 0.004079
1 0.964244 0.006169
1 0.947231 0.008434
1 0.929323 0.010765
1 0.910956 0.013101
1 0.892372 0.01542
1 0.873723 0.0177
1 0.855041 0.019931
1 0.836311 0.022119
1 0.817558 0.024266
1 0.798819 0.026366
1 0.780088 0.028414
1 0.761336 0.030413
1 0.74256 0.03237
1 0.72378 0.034284
1 0.705012 0.036149
1 0.686255 0.037964
1 0.667502 0.039728
1 0.648751 0.04144
1 0.630004 0.043098
1 0.611266 0.044701
1 0.592538 0.046245
1 0.573821 0.047728
1 0.555117 0.049149
1 0.53643 0.050503
1 0.517763 0.051786
1 0.499117 0.052996
1 0.480488 0.054127
1 0.461875 0.055178
1 0.443287 0.056144
1 0.42474 0.057019
1 0.406241 0.057796
1 0.387789 0.058466
1 0.369372 0.059023
1 0.350989 0.059462
1 0.332648 0.059779
1 0.314366 0.059965
1 0.296159 0.060009
1 0.278033 0.059903
1 0.259997 0.059634
1 0.24206 0.059191
1 0.224236 0.058562
1 0.206544 0.057733
1 0.189011 0.056692
1 0.171676 0.055421
1 0.154596 0.053909
1 0.137852 0.052138
1 0.121548 0.050098
1 0.105827 0.047785
1 0.090903 0.04522
1 0.077039 0.042449
1 0.064541 0.039548
1 0.053594 0.036612
1 0.044211 0.033717
1 0.036254 0.030913
1 0.029567 0.028218
1 0.023982 0.025653
1 0.01931 0.023217
1 0.015371 0.020871
1 0.012012 0.018579
1 0.009117 0.016316
1 0.006653 0.014058
1 0.004621 0.011797
1 0.003007 0.009544
1 0.001777 0.007318
1 0.000894 0.005155
1 0.000322 0.003059
1 0.000036 0.001014
1 0.000036 -0.001014
1 0.000322 -0.003059
1 0.000894 -0.005155
1 0.001777 -0.007318
1 0.003007 -0.009544
1 0.004621 -0.011797
1 0.006653 -0.014058
1 0.009117 -0.016316
1 0.012012 -0.018579
1 0.015371 -0.020871
1 0.01931 -0.023217
1 0.023982 -0.025653
1 0.029567 -0.028218
1 0.036254 -0.030913
1 0.044211 -0.033717
1 0.053594 -0.036612
1 0.064541 -0.039548
1 0.077039 -0.042449
1 0.090903 -0.04522
1 0.105827 -0.047784
1 0.121548 -0.050098
1 0.137852 -0.052138
1 0.154596 -0.053909
1 0.171676 -0.055421
1 0.189011 -0.056692
1 0.206544 -0.057733
1 0.224236 -0.058562
1 0.24206 -0.059191
1 0.259997 -0.059634
1 0.278033 -0.059903
1 0.296159 -0.060009
1 0.314366 -0.059965
1 0.332648 -0.059779
1 0.350989 -0.059462
1 0.369372 -0.059023
1 0.387789 -0.058466
1 0.406241 -0.057796
1 0.42474 -0.057019
1 0.443287 -0.056144
1 0.461875 -0.055178
1 0.480488 -0.054127
1 0.499117 -0.052996
1 0.517763 -0.051786
1 0.53643 -0.050503
1 0.555117 -0.049149
1 0.573821 -0.047728
1 0.592538 -0.046245
1 0.611266 -0.044701
1 0.630004 -0.043098
1 0.648751 -0.04144
1 0.667502 -0.039728
1 0.686255 -0.037964
1 0.705012 -0.036149
1 0.72378 -0.034284
1 0.74256 -0.03237
1 0.761336 -0.030413
1 0.780088 -0.028414
1 0.798819 -0.026366
1 0.817558 -0.024266
1 0.836311 -0.022119
1 0.855041 -0.019931
1 0.873723 -0.0177
1 0.892372 -0.01542
1 0.910956 -0.013101
1 0.929323 -0.010765
1 0.947231 -0.008434
1 0.964244 -0.006169
1 0.979641 -0.004079
1 0.992704 -0.002274
1 1 -0.00126
1 1 0.00126Import this coordinates in SpaceClaim and the geometry can easily be drawn.
The geometry
The domain or the enclosure for the simulation.
Velocity component at inlet (X): 51.21m/s
Velocity component at inlet (Y): 9.029m/s
Results
Pressure Contour
Velocity Contour
Scaled Residuals
Coefficient of Drag Plot
Coefficient of Lift Plot
CASE 3
The angle of Attack: 15 degrees
Velocity component at inlet (X): 50.22m/s
Velocity component at inlet (Y): 13.45m/s
Results
Static Pressure Contour
Velocity Contour
Residual Plot
Coefficient of Drag Plot
Coefficient of Lift Plot
SUPERSONIC FLOW
CASE 1
Angle of Attack: 5 degrees
Velocity component at inlet (X): 398.477 m/s
Velocity component at inlet (Y): 34.862 m/s
Results
Velocity Contour
Pressure Contour
Scaled Residuals
Coefficient Of Lift Plot
Coefficient of Drag Plot
CASE 2
Angle of Attack: 10 degrees
Velocity component at inlet (X): 393.923 m/s
Velocity component at inlet (Y): 69.459 m/s
RESULTS
Pressure Contour
Velocity Contour
Scaled Residuals
Coefficient of Lift Plot
Coefficient of Drag Plot
CASE 3
Angle of Attack: 15 degrees
Velocity component at inlet (X): 386.3703 m/s
Velocity component at inlet (Y): 103.527 m/s
RESULTS
Pressure Plot
Velocity Contour
Scaled Residuals
Coefficient of Lift Plot
Final Results
| Angle of Attack | Subsonic | Flow | Supersonic | Flow |
| (degrees) | Drag Coefficient | Lift Coefficient | Drag Coefficient | Lift Coefficient |
| 5 | 0.01523 | 0.2194 | 0.0301 | 0.1820 |
| 10 | 0.04462 | 0.4392 | 0.0430 | 0.4272 |
| 15 | 0.00091 | 0.0618 | 0.0887 | 0.6035 |