AerodynamicInformation¶
Aerodynamic information needed to build a case
Note
It should be defined after the StructuralInformation of the case
This function concatenates aerodynamic properties to be writen in the same h5 File
Parameters: *args – list of AerodynamicInformation() to be meged into ‘self’
Changes the discretization of the matrix of airfoil coordinates
Parameters: - airfoils (np.array) – Matrix with the x-y coordinates of all the airfoils to be modified
- new_num_nodes (int) – Number of points that the output coordinates will have
Returns: Matrix with the x-y coordinates of all the airfoils with the new discretization
Return type: new_airfoils (np.array)
Check some properties of the AerodynamicInformation()
Notes
These conditions have to be to correctly define a case but they are not the only ones
Returns a copy of the object
Returns: new object with the same properties Return type: copied(AerodynamicInformation)
Defines the whole case from the appropiated variables in vector form (associated to nodes)
Parameters: - StructuralInformation (StructuralInformation) – Structural infromation of the case
- vec_aero_node (np.array) – defines if a node has aerodynamic properties or not
- vec_chord (np.array) – chord of the nodes
- vec_twist (np.array) – twist of the nodes
- vec_sweep (np.array) – sweep of the nodes
- vec_surface_m (np.array) – Number of panels in the chord direction
- vec_surface_distribution (np.array) – Surface at which each element belongs
- vec_m_distribution (np.array) – distribution of the panels along the chord
- vec_elastic_axis (np.array) – position of the elastic axis in the chord
- vec_airfoil_distribution (np.array) – airfoil at each element node
- airfoils (np.array) – coordinates of the camber lines of the airfoils
Defines the whole case from the appropiated variables constant at every point
Parameters: - StructuralInformation (StructuralInformation) – Structural infromation of the case
- chord (float) – chord
- twist (float) – twist
- sweep (float) – sweep
- num_chord_panels (int) – Number of panels in the chord direction
- m_distribution (str) – distribution of the panels along the chord
- elastic_axis (float) – position of the elastic axis in the chord
- num_points_camber (int) – Number of points to define the camber line
- airfoils (np.array) – coordinates of the camber lines of the airfoils
Writes the h5 file with the aerodynamic information
Parameters: - route (string) – path of the case
- case_name (string) – name of the case
Defines the whole case from the appropiated variables
Parameters: - aero_node (np.array) – defines if a node has aerodynamic properties or not
- chord (np.array) – chord of the elements
- twist (np.array) – twist of the elements
- sweep (np.array) – sweep of the elements
- surface_m (np.array) – Number of panels in the chord direction
- surface_distribution (np.array) – Surface at which each element belongs
- m_distribution (str) – distribution of the panels along the chord
- elastic_axis (np.array) – position of the elastic axis in the chord
- airfoil_distribution (np.array) – airfoil at each element node
- airfoils (np.array) – coordinates of the camber lines of the airfoils
Create the camber of the airfoil at each node position from the camber of the pure airfoils present in the blade
Parameters: - pure_airfoils_camber (np.array) – xy coordinates of the camber lines of the pure airfoils
- r_pure_airfoils (np.array) – radial position of the pure airfoils
- r (np.array) – radial positions to compute the camber lines through linear interpolation
Returns: camber lines at the new radial positions
Return type: airfoils_camber (np.array)
Create the camber of the airfoil at each node position from the camber of the pure airfoils present in the blade based on the thickness
Parameters: - pure_airfoils_camber (np.array) – xy coordinates of the camber lines of the pure airfoils
- thicknesss_pure_airfoils (np.array) – thickness of the pure airfoils
- blade_thickness (np.array) – thickness of the blade positions
Returns: camber lines at the new radial positions
Return type: airfoils_camber (np.array)
Sets to zero all the variables
Parameters: - num_node_elem (int) – number of nodes per element
- num_node (int) – number of nodes
- num_elem (int) – number of elements
- num_airfoils (int) – number of different airfoils
- num_surfaces (int) – number of aerodynamic surfaces
- num_points_camber (int) – number of points to define the camber line of the airfoil