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
- param structural_kstep
Current structural substep
- type structural_kstep
- 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
- keyword correct_lift
correct also lift coefficient according to the polars
- kwtype correct_lift
bool
- keyword cd_from_cl
interpolate drag from lift instead of computing the AoA first
- kwtype cd_from_cl
bool
- returns
corresponding aerodynamic force at the structural node from the force and moment at a grid vertex
- rtype
np.ndarray