polarsΒΆ
This function corrects the aerodynamic forces from UVLM based on the airfoil polars provided by the user in the aero.h5 file
These are the steps needed to correct the forces:
- The force coming from UVLM is divided into induced drag (parallel to the incoming flow velocity) and lift (the remaining force).
- The angle of attack is computed based on that lift force and the angle of zero lift computed form the airfoil polar and assuming a slope of \(2 \pi\)
- The drag force is computed based on the angle of attack and the polars provided by the user
| param data: | SHARPy data |
|---|---|
| type data: | sharpy.PreSharpy |
| param aero_kstep: | |
| Current aerodynamic substep | |
| type aero_kstep: | |
sharpy.utils.datastructures.AeroTimeStepInfo |
|
| param structural_kstep: | |
| Current structural substep | |
| type structural_kstep: | |
sharpy.utils.datastructures.StructTimeStepInfo |
|
| param struct_forces: | |
| Array with the aerodynamic forces mapped on the structure in the B frame of reference | |
| type struct_forces: | |
| np.array | |
| keyword rho: | air density |
| kwtype rho: | float |
| returns: | corresponding aerodynamic force at the structural node from the force and moment at a grid vertex |
| rtype: | np.ndarray |