BladeAD.core.BEM.bem_model
Module Contents
Classes
Blade Element Momentum (BEM) model. |
- class BladeAD.core.BEM.bem_model.BEMModel(num_nodes: int, airfoil_model, integration_scheme: str = 'trapezoidal', tip_loss: bool = True)
Blade Element Momentum (BEM) model.
- Parameters
- num_nodesint
Number of nodes.
- airfoil_modelAirfoilModel
Airfoil model.
- integration_schemestr
Integration scheme for thrust and torque computation. Options are ‘Simpson’, ‘Riemann’, ‘trapezoidal’. Default is ‘trapezoidal’.
- tip_lossbool
Include tip loss. Default is True.
- evaluate(inputs: BladeAD.utils.var_groups.RotorAnalysisInputs, ref_point: Union[csdl_alpha.Variable, numpy.ndarray] = np.array([0.0, 0.0, 0.0])) BladeAD.utils.var_groups.RotorAnalysisOutputs
Evaluate the BEM solver.
- Parameters
- inputsRotorAnalysisInputs
Input variables. Includes quantities like rpm, mesh_parameters, mesh_velocity, etc.
- ref_pointUnion[csdl.Variable, np.ndarray], optional
Reference point for computing moments, by default np.array([0., 0., 0.])
- Returns
- RotorAnalysisOutputs (dataclass)
Output variables. Includes quanties like total/sectional thrust, total/sectional torque, etc.