Hello everyone! I am running a 3D simulation of UAV(Unmanned Aerial Vehicle) at Mach ~0.04. However when i plot the cd vs alpha(-15 to 15) im getting unrealistic values. Could anyone look into it? Would be a great help! For example im getting low Cd at high alpha. Attached below are the results. Runs and their corresponding angle of attack are as: Boundary conditions are velocity inlet, pressure outlet, wall at the uav surface free stream on the 4 remaining enclosure faces
| 29 | -14 |
|---|---|
| 27 | -13 |
| 25 | -12 |
| 23 | -11 |
| 21 | -10 |
| 19 | -9 |
| 17 | -8 |
| 15 | -7 |
| 13 | -6 |
| 11 | -5 |
| 9 | -4 |
| 7 | -3 |
| 5 | -2 |
| 3 | -1 |
| 1 | 0 |
| 2 | 1 |
| 4 | 2 |
| 6 | 3 |
| 8 | 4 |
| 10 | 5 |
| 12 | 6 |
| 14 | 7 |
| 16 | 8 |
| 18 | 9 |
| 20 | 10 |
| 22 | 11 |
| 24 | 12 |
| 26 | 13 |
| 28 | 14 |
| 30 | 15 |
