AerodynamicInformation

class sharpy.utils.generate_cases.AerodynamicInformation

Aerodynamic information needed to build a case

Note

It should be defined after the StructuralInformation of the case

assembly_aerodynamics(*args)

This function concatenates aerodynamic properties to be writen in the same h5 File

Parameters

*args – list of AerodynamicInformation() to be meged into ‘self’

change_airfoils_discretezation(airfoils, new_num_nodes)

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_AerodynamicInformation(StructuralInformation)

Check some properties of the AerodynamicInformation()

Notes

These conditions have to be to correctly define a case but they are not the only ones

copy()

Returns a copy of the object

Returns

new object with the same properties

Return type

copied(AerodynamicInformation)

create_aerodynamics_from_vec(StructuralInformation, vec_aero_node, vec_chord, vec_twist, vec_sweep, vec_surface_m, vec_surface_distribution, vec_m_distribution, vec_elastic_axis, vec_airfoil_distribution, airfoils, user_defined_m_distribution=None)

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

create_one_uniform_aerodynamics(StructuralInformation, chord, twist, sweep, num_chord_panels, m_distribution, elastic_axis, num_points_camber, airfoil)

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

generate_aero_file(route, case_name, StructuralInformation)

Writes the h5 file with the aerodynamic information

Parameters

• route (string) – path of the case

• case_name (string) – name of the case

generate_full_aerodynamics(aero_node, chord, twist, sweep, surface_m, surface_distribution, m_distribution, elastic_axis, airfoil_distribution, airfoils)

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

interpolate_airfoils_camber(pure_airfoils_camber, r_pure_airfoils, r, n_points_camber)

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)

interpolate_airfoils_camber_thickness(pure_airfoils_camber, thickness_pure_airfoils, blade_thickness, n_points_camber)

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)

set_to_zero(num_node_elem, num_node, num_elem, num_airfoils=1, num_surfaces=0, num_points_camber=100)

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