Detailed Documentation#
This page provides a detailed description of the turbine model and its components. The turbine model is defined in the turbine_schema.yaml file, which is located in the windIO/schemas/turbine directory. The schema is written in YAML format and is used to validate the turbine model. The schema is also used to generate this documentation for the turbine model.
Type: objectOntology definition for wind turbines
No Additional PropertiesUnique identifier of the wind turbine model
Version of windIO used
The field assembly includes nine entries that aim at describing the overall configuration of the wind turbine
IEC wind class. The entry should be I, II, III, or IV.
Must be one of:
- "I"
- "II"
- "III"
- "IV"
- "i"
- "ii"
- "iii"
- "iv"
- 1
- 2
- 3
- 4
IEC turbulence class of the wind turbine. The options are A, B, C, and D.
Must be one of:
- "A"
- "B"
- "C"
- "D"
- "a"
- "b"
- "c"
- "d"
Drivetrain configuration. This is intended to inform an automated interpreter of the yaml about the data specified in the field drivetrain
Switch between upwind and downwind rotor configurations.
Must be one of:
- "Upwind"
- "upwind"
- "UPWIND"
- "downwind"
- "Downwind"
- "DOWNWIND"
Number of blades of the rotor
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 10
Diameter of the wind turbine rotor. It is defined as two times the sum of hub radius and blade length along the z direction times the cosine of the rotor precone. In formula, this is 2 x (Rhub + blade length along z) * cos(precone). This definition is consistent with commercial aeroelastic solvers. It is not consistent with OpenFAST, which takes into account the instantaneous blade deflection.
Units: m
Value must be greater or equal to 0 and lesser or equal to 1000
Height of the hub center over the ground (land-based) or the mean sea level (offshore)
Units: m
Value must be greater or equal to 0 and lesser or equal to 1000
Nameplate power of the turbine, i.e. the rated electrical output of the generator.
Units: W
Value must be greater or equal to 0
Turbine design lifetime in years.
Units: yr
Value must be greater or equal to 0
Nested dictionary structure of components describing the wind turbine assembly
The component blade includes three subcomponents, namely reference_axis, outer_shape, and structure. All distributed quantities, such as blade chord or the thickness of a structural component, are expressed in terms of pair arrays grid and values, which must have a minimum length of two elements and the same size. grid is defined nondimensional between 0 (root) and 1 (tip) along the, usually curved, reference_axis.
The aerodynamic, structural, and elastic characteristics of the wind turbine blade are defined at a common reference axis. The axis is defined with sets of x, y, and z points. The reference system for x, y, and z is located at blade root, with z aligned with the pitch axis, x pointing towards the suction sides of the airfoils (standard prebend will be negative) and y pointing to the trailing edge (standard sweep will be positive). The blade main direction is expressed along z, and total blade length must be computed integrating the fields x, y, and z three-dimensionally.
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to 0.0 and lesser or equal to 1.0
No Additional Items
Each item of this array must be:
Units: m
The field outer_shape consists of a dictionary containing the data describing the outer shape of the blade.
Chord in meters along blade span.
Geometric twist of the local cross-sections along the blade span in degrees. Twist is generally positive toward blade root, and may become negative toward blade tip. Aerodynamic properties and equivalent elastic properties of the blade are defined with respect to this distribution of twist.
No Additional Items
Each item of this array must be:
Units: deg
Relative thickness, expressed between 0 (flat plate) and 1 (cylinder), along blade span.
The field section_offset_y controls the airfoil position relative to the reference axis, by specifying the distance in meters along the chordline from the reference axis to the leading edge. 0 means that the airfoil is pinned at the leading edge, a positive offset means that the leading edge is upstream of the reference axis in local chordline coordinates, and a negative offset that the leading edge aft of the reference axis.
The field section_offset_x controls the airfoil position relative to the reference axis, by specifying the chordline normal distance in meters from the reference axis. 0 means that the reference axis lies on the airfoil chordline, a positive offset means that the chordline is shifted in the direction of the suction side relative to the reference axis, and a negative offset that the section is shifted in the direction of the pressure side of the airfoil.
List of airfoils and corresponding polars adopted along blade span. The airfoil positions must correspond to the rthick field. For each airfoil, their spanwise position can be defined (if not defined rthick will be used, if both are defined rthick should dominate). Also, for each airfoil different sets of polars can be defined with an associated weight. The array of weights must sum up to 1. The weights help blend different polar sets, for example a 70% free transition / 30% fully turbulent.
Each item of this array must be:
Name of the airfoil, must be available in the airfoil database
Spanwise position defined between 0 (root) and 1 (tip) along the curved reference axis.
Value must be greater or equal to 0.0 and lesser or equal to 1.0
Tags corresponding to polar sets defined for this airfoil
No Additional ItemsEach item of this array must be:
Weights, defined between 0 and 1 and summing up to 1, defining the blending of the different sets of polars
No Additional ItemsEach item of this array must be:
Value must be greater or equal to 0.0 and lesser or equal to 1.0
Outer aerodynamic surface of the blade formatted as block structured arrays with x, y, z coordinates mapped onto the curvilinear grid used for the reference axis. The following steps must be followed in the right order. 1) From the outershape field, use rthick or use PCHIP based on the master airfoils and the outershape.airfoils.spanwiseposition grid to interpolate airfoil cross-sections in between defined airfoils. Note that using airfoilposition in the windIO file requires the resolution of this grid to be quite fine, and airfoils with relative thickness above the typical 36% to be defined. Otherwise it is quite difficult to control the shape transition from the cylindrical root to the max chord. Also note that airfoils in the airfoils section should be interpolated onto a common grid based on normalized surface curve fraction using PCHIP, allowing point-wise interpolation between airfoils. Interpolating based on a common chord-wise discretization will result in very different airfoil shapes particularly for thick airfoils. 2) Scale airfoils by chord. 3) In the blade root coordinate system, apply sectionoffsety from the leading edge along the chord. 4) In the blade root coordinate system, apply sectionoffsetx from the chord line normal to chord. 5) Compute and apply rotation matrix M to place airfoils orthonormal to local reference axis tangent. 6) Apply x, y and z translations from the curved reference axis. The transformation matrix M for a cross-section is constructed as 1) compute reference axis curve tangent unit vectors (tx, ty, tz) (preferably analytically using pchip derivatives) 1) compute rotation matrices for x- and y-rotations Mx and My from axis and angle, see https://en.wikipedia.org/wiki/Rotation_matrix "Rotation matrix from axis and angle" 3) Mxy = matmul (My, Mx) 4) Compute twist correction rz = atan2(Mxy(0,1), Mxy(0,0)) 5) rz = twist + rz 6) Compute z-rotation matrix Mz as for step 2 from tz and rz 7) M = matmul (Mx, My). The above definition of the transformation from local to blade reference frame is described better here https://iopscience.iop.org/article/10.1088/1742-6596/2767/2/022033/pdf. Also see https://wes.copernicus.org/articles/7/1341/2022/wes-7-1341-2022.pdf.
No Additional Items
Each item of this array must be:
No Additional Items
Each item of this array must be:
No Additional Items
Each item of this array must be:
No Additional Items
Each item of this array must be:
No Additional Items
Each item of this array must be:
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The field structure contains the data to describe the internal structure of standard wind turbine blades. This is a fairly sophisticated process and the ontology proposed in this work supports different definitions. On the top level, the field structure has two sub-components, namely the webs, where the positions of the shear webs are defined, and the layers, which describe all internal layers in terms of name, material, thickness, number of plies n_plies, fiber_orientation (for composites), and position in the two-dimensional sections. Recently, the fields joint and root were added to support blades that are segmented spanwise and details about the blade root bolting.
The field anchors defines non-dimensional arc positions along the surface of the blade that are used to position shear webs and layers. The anchors are defined in terms of name, start_nd_arc, and optionally end_nd_arc. In addition to the required arc positions, anchors can also be defined parametrically using the offset_arc, offset_nd_arc or plane_intersection.
Each item of this array must be:
String that identifies the anchor.
Non-dimensional arc position of the anchor which can be defined using grid/values or as a reference to another anchor.
Non-dimensional location of the point along the non-dimensional arc length
Grid along an arc length, expressed non dimensionally where 0 is the trailing edge on the suction side and 1 is the trailing edge on the pressure side. The arc starts and ends at the mid-point of the trailing edge in the case of open trailing edges.
No Additional ItemsEach item of this array must be:
Units: dimensionless
Value must be greater or equal to -1.0 and lesser or equal to 1.0
Optional additional non-dimensional arc position of the anchor which can be defined using grid/values or as a reference to another anchor.
Non-dimensional location of the point along the non-dimensional arc length
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i1Optional midpoint non-dimensional arc position of the anchor which can be defined using grid/values or as a reference to another anchor.
Non-dimensional location of the point along the non-dimensional arc length
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i1Defines an offset arc relative to another anchor.
Specifies the arc type being defined (e.g., start_nd_arc or end_nd_arc).
Must be one of:
- "start_nd_arc"
- "end_nd_arc"
Defines a normalized offset arc relative to another anchor.
Specifies the arc type being defined (e.g., start_nd_arc or end_nd_arc).
Must be one of:
- "start_nd_arc"
- "end_nd_arc"
Non-dimensional location of the point along the non-dimensional arc length
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i1width of the anchor in meters used when both startndarc and endndarc are defined.
No Additional Items
Each item of this array must be:
Must be one of:
- "start_nd_arc"
- "end_nd_arc"
Defines a plane intersection for computing the arc position(s) of the anchor.
The field side is a string that defines the side where the intesection should be performed. It can be either suction, pressure, or both.
Must be one of:
- "suction"
- "pressure"
- "both"
The field defines is a list of strings that defines the anchors the intersection computes.
Each item of this array must be:
Must be one of:
- "start_nd_arc"
- "end_nd_arc"
- "midpoint_nd_arc"
The field plane_type1 is a dictionary that defines a plane intersection for computing the arc position(s) of the anchor. It is constructed as follows, 1. Starting from the blade root coordinate system, rotate the lofted blade by the amount defined in rotation around the blade z-axis using a right-handed rule. 2. Interpolate the x, y, z coordinates of the anchor_curve curve at the anchors_nd_grid non-dimensional arc positions, resulting in two points in space. 3. Construct a plane spanning the two points, and with a normal vector in the y-z plane perpendicular to the line connecting the two points. 4. Offset the plane along the plane normal vector by the amount defined in offset. If the offset is not linear, the plane effectively becomes a ruled surface. 5. Intersect the plane with the blade surface and compute the position_nd_arc of the intersection curve along the span.
The field anchor_curve is a string that identifies the reference anchor curve from which the plane is generated.
Grid positions for computing the two plane points between which the intersection plane is generated.
Must contain a minimum of 2 items
Must contain a maximum of 2 items
Each item of this array must be:
The field rotation defines the rotation of the plane in degrees.
Units: deg
The field plane_type2 is a dictionary that defines a ruled surface intersection for computing the arc position(s) of the anchor. 1. Starting from the blade root coordinate system, rotate the lofted blade by the amount defined in rotation around the blade root z-axis using a right-handed rule. 2. In the y-z plane construct an offset curve normal to the anchor curve. 3. Construct the ruled surface by extrapolating the offset curve along the x-axis. 4. Intersect the ruled surface with the blade surface and compute the position_nd_arc of the intersection curve.
The field rotation is a number that defines the rotation of the plane in degrees.
Units: deg
The field webs consists of a list of entries, each representing a shear web defined in terms of name and position. Shear webs are assumed to be planar surfaces connecting the suction and pressure sides of the blade.
Each item of this array must be:
String that identifies the web.
The field anchors in a web defines positions along the web surface for placing web layers.
Each item of this array must be:
String that identifies the anchor.
Non-dimensional location of the point along the non-dimensional arc length
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i1Non-dimensional location of the point along the non-dimensional arc length
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i1The field flanges defines the geometry and bondline thickness of the flanges of a shear web. The flanges are defined in terms of type, side, bondline, start_nd_arc, and end_nd_arc.
Each item of this array must be:
The field type is a string that defines the shape of the flange, either L-shaped or T-shaped.
Must be one of:
- "L"
- "T"
Must be one of:
- "suction"
- "pressure"
- "both"
The field bondline is a dictionary that defines the bondline material and thickness.
material name identifier, which needs to be defined in the materials section.
thickness of the bondline in meters described as function of spanwise grid
The field start_nd_arc is a reference to the anchor that defines the start of the flange attachment on the shell. The anchor refers to an anchor on the shell surface and must be defined in the anchors section.
The field end_nd_arc is a reference to the anchor that defines the end of the flange attachment on the shell. The anchor refers to an anchor on the shell surface and must be defined in the anchors section.
The sub-field layers defines the material layers of the wind turbine blade. In most cases, these are layers of composite materials. The thickness is defined in meters and optionally with the number of plines using the field n_plines.
Each item of this array must be:
String that identifies the layer.
String that identifies the material of the layer. The material and its properties must be defined in the top-level materials.
web to which the layer is associated to, only to be defined for web layers
Dimensional thickness of the laminate, expressed in meters. This value is most commonly modeled constant along the section but can also be defined as a 2D grid in the spanwise and chordwise direction allowing to define tapering of a layer, relevant for core material in the trailing edge.
A 2D array specifying the grid points where the first row is the spanwise grid and following rows the grid along the arc of the airfoil.
No Additional ItemsEach item of this array must be:
Units: dimensionless
Must contain a minimum of 2 items
Each item of this array must be:
Units: dimensionless
An array specifying the thickness values on the 2D grid defined by the grid2d field. Note that the thickness array has to contain one less row than the grid2d field.
Must contain a minimum of 2 items
Each item of this array must be:
Units: m
Each item of this array must be:
Units: m
In addition or in alternative to the dimensional thickness, the discrete number of plies of a composite laminate can be defined by the user. Notably, the ply thickness is a material property (not a layer property) and it is defined in the top-level field materials.
Non dimensional quantity described along a beam and expressed non-dimensional
No Additional ItemsEach item of this array must be:
Units: dimensionless
For composite laminates, the orientation of the fibers in degrees can be specified. Looking from blade root, positive angles represent a rotation of the fibers towards the leading edge of the blade. Note that the angles are with respect to the cross section local reference system, not the reference system at blade root.
The field start_nd_arc is a reference to the anchor that defines the start of the layer. The anchor is defined in terms of name, start_nd_arc, and end_nd_arc.
The field end_nd_arc is a reference to the anchor that defines the end of the layer. The anchor is defined in terms of name, start_nd_arc, and end_nd_arc.
The trailing edge adhesive fills the void on the inside of the shell at the trailing edge, and its location is defined by four corners, two on the suction sice and two on the pressure side.
Material name identifier, which needs to be defined in the :code:materials section.
defines the start of the trailing edge adhesive on the suction side closest to the trailing edge.
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i0defines the end of the trailing edge adhesive on the suction side.
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i0defines the start of the trailing edge adhesive on the pressure side closest to the trailing edge.
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i0defines the end of the trailing edge adhesive on the pressure side.
Same definition as components_blade_structure_anchors_items_start_nd_arc_oneOf_i0This is a spanwise joint along the blade, usually adopted to ease transportation constraints
Spanwise position of the segmentation joint.
Units: dimensionless
Value must be greater or equal to 0.0 and lesser or equal to 1.0
Mass of the joint.
Units: kg
Value must be greater or equal to 0.0 and lesser or equal to 1000000.0
Cost of the joint.
Units: USD
Value must be greater or equal to 0.0 and lesser or equal to 1000000.0
Diameter of the fastener, default is M30, so 0.03 meters
Units: m
Value must be greater or equal to 0.01 and lesser or equal to 0.2
Max stress on bolt
Units: Pa
Value must be greater or equal to 100000.0 and lesser or equal to 10000000000.0
The equivalent elastic properties of a beam are defined in elastic_properties. Here, 6x6 stiffness and mass matrices are defined. Out of 36 entries of the matrices, given the symmetry, the yaml file requires the definition of only 21 values as inputs for the stiffness matrix, whereas the inertia matrix is defined in terms of unit mass, coordinates of the center of mass, and mass moments of inertia. For the blade, these properties are defined with respect to the aerodynamic twist, which is the same as structural twist.
Distribution of the K11 element of the stiffness matrix along blade span. K11 corresponds to the shear stiffness along the x axis (in a blade, x points to the trailing edge)
No Additional ItemsEach item of this array must be:
Distribution of the K22 element of the stiffness matrix along blade span. K22 corresponds to the shear stiffness along the y axis (in a blade, y points to the suction side)
No Additional ItemsEach item of this array must be:
Distribution of the K33 element of the stiffness matrix along blade span. K33 corresponds to the axial stiffness along the z axis (in a blade, z runs along the span and points to the tip)
No Additional ItemsEach item of this array must be:
Distribution of the K44 element of the stiffness matrix along blade span. K44 corresponds to the bending stiffness around the x axis (in a blade, x points to the trailing edge and K44 corresponds to the flapwise stiffness)
No Additional ItemsEach item of this array must be:
Distribution of the K55 element of the stiffness matrix along blade span. K55 corresponds to the bending stiffness around the y axis (in a blade, y points to the suction side and K55 corresponds to the edgewise stiffness)
No Additional ItemsEach item of this array must be:
Distribution of K66 element of the stiffness matrix along blade span. K66 corresponds to the torsional stiffness along the z axis (in a blade, z runs along the span and points to the tip)
No Additional ItemsEach item of this array must be:
Distribution of the K12 element of the stiffness matrix along blade span. K12 is a cross term between shear terms
No Additional ItemsEach item of this array must be:
Distribution of the K13 element of the stiffness matrix along blade span. K13 is a cross term shear - axial
No Additional ItemsEach item of this array must be:
Distribution of the K14 element of the stiffness matrix along blade span. K14 is a cross term shear - bending
No Additional ItemsEach item of this array must be:
Distribution of the K15 element of the stiffness matrix along blade span. K15 is a cross term shear - bending
No Additional ItemsEach item of this array must be:
Distribution of the K16 element of the stiffness matrix along blade span. K16 is a cross term shear - torsion
No Additional ItemsEach item of this array must be:
Distribution of the K23 element of the stiffness matrix along blade span. K23 is a cross term shear - axial
No Additional ItemsEach item of this array must be:
Distribution of the K24 element of the stiffness matrix along blade span. K24 is a cross term shear - bending
No Additional ItemsEach item of this array must be:
Distribution of the K25 element of the stiffness matrix along blade span. K25 is a cross term shear - bending
No Additional ItemsEach item of this array must be:
Distribution of the K26 element of the stiffness matrix along blade span. K26 is a cross term shear - torsion
No Additional ItemsEach item of this array must be:
Distribution of the K34 element of the stiffness matrix along blade span. K34 is a cross term axial - bending
No Additional ItemsEach item of this array must be:
Distribution of the K35 element of the stiffness matrix along blade span. K35 is a cross term axial - bending
No Additional ItemsEach item of this array must be:
Distribution of the K36 element of the stiffness matrix along blade span. K36 is a cross term axial - torsion
No Additional ItemsEach item of this array must be:
Distribution of the K45 element of the stiffness matrix along blade span. K45 is a cross term flapwise bending - edgewise bending
No Additional ItemsEach item of this array must be:
Distribution of the K46 element of the stiffness matrix along blade span. K46 is a cross term flapwise bending - torsion
No Additional ItemsEach item of this array must be:
Distribution of the K56 element of the stiffness matrix along blade span. K56 is a cross term edgewise bending - torsion
No Additional ItemsEach item of this array must be:
Mass per unit length along the beam, expressed in kilogram per meter
No Additional ItemsEach item of this array must be:
Units: kg/m
Distance between the reference axis and the center of mass along the x axis
Same definition as valuesDistance between the reference axis and the center of mass along the y axis
Same definition as valuesEdgewise mass moment of inertia per unit span (around y axis)
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Value must be greater or equal to 0
Flapwise mass moment of inertia per unit span (around x axis)
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Value must be greater or equal to 0
Polar moment of inertia per unit span (around z axis). Please note that for beam-like structures iplr must be equal to iedge plus iflap.
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Value must be greater or equal to 0
Sectional cross-product of inertia per unit span (cross term x y)
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Structural damping of the beam. For now, viscous damping is included
Six damping coefficients to model viscous damping, where the damping forces are proportional to the strain rate
No Additional ItemsEach item of this array must be:
Point masses distributed along the beam, expressed in kilogram. These can be used to model features such as flanges.
No Additional ItemsEach item of this array must be:
Units: kg
This is the outer diameter of the hub. It is also the diameter of the circle centered at the rotor apex and connecting the blade root centers.
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 30.0
Rotor precone angle, defined positive for both upwind and downwind rotors.
Units: deg
Value must be greater or equal to 0 and lesser or equal to 50
Equivalent drag coefficient to compute the aerodynamic forces generated on the hub.
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 2.0
Rigid body modeling the full hub system, which includes the hub, the spinner, the blade bearings, the pitch actuators, the cabling. The properties are defined in the hub-aligned coordinate system, which is centered at the rotor apex and has x aligned along the (possibly tilted) shaft, y parallel to the ground, and z pointing upwards (including the rotor tilt). The rotational inertia of the hub system is around x, so the first term of the inertia vector.
Mass of the component modeled as a rigid body.
Units: kg
Value must be greater or equal to 0.0
Mass moment of inertia of the component modeled as a rigid body.
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Location of the rigid body with respect to the coordinate system.
No Additional ItemsEach item of this array must be:
Units: m
Additional Properties of any type are allowed.
Type: objectGeometrical metrics describing the drivetrain. Currently, these are inputs to WISDEM specific drivetrain sizing tool, DrivetrainSE
Tilt angle of the nacelle, always defined positive.
Units: deg
Value must be greater or equal to 0.0 and lesser or equal to 20.0
Vertical distance between the tower top and the hub center.
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
Distance from hub flange to first main bearing along shaft.
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
Distance from first to second main bearing along shaft.
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
Horizontal distance between the tower axis and the rotor apex.
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
Equivalent drag coefficient to compute the aerodynamic forces generated on the hub.
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 2.0
Inputs describing the gearbox, when present
Gear ratio of the drivetrain. Set it to 1 for direct drive machines.
Units: dimensionless
Value must be greater or equal to 1 and lesser or equal to 1000
User input override of gearbox length along shaft, only used when using gearboxmassuser is > 0
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
User input override of gearbox radius, only used when using gearboxmassuser is > 0
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
User input override of gearbox mass
Units: kg
Value must be greater or equal to 0.0 and lesser or equal to 1000000000.0
Efficiency of the gearbox system.
Units: dimensionless
Value must be greater or equal to 0.8 and lesser or equal to 1.0
Damping ratio for the drivetrain system
Units: dimensionless
Value must be greater or equal to 0.0 and lesser or equal to 1.0
3-letter string of Es or Ps to denote epicyclic or parallel gear configuration
Number of planets for epicyclic stages (use 0 for parallel)
No Additional ItemsEach item of this array must be:
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 6
Equivalent torsional stiffness of the gearbox. This parameter is often required by aeroelastic solvers
Units: N*m/rad
Value must be greater or equal to 0
Equivalent torsional damping of the gearbox. This parameter is often required by aeroelastic solvers
Units: N*m/(rad/s)
Value must be greater or equal to 0
Mass of the component modeled as a point
Units: kg
Value must be greater or equal to 0
Mass moment of inertia of the component modeled as a point. The inertia is defined at the center of mass.
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Location of the rigid body with respect to the coordinate system
No Additional ItemsEach item of this array must be:
Units: m
Inputs describing the low speed shaft
Length of the low speed shaft
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 10.0
Diameter of the low speed shaft at beginning (generator/gearbox) and end (hub) points
No Additional ItemsEach item of this array must be:
Units: m
Thickness of the low speed shaft at beginning (generator/gearbox) and end (hub) points
No Additional ItemsEach item of this array must be:
Units: m
Material name identifier
Inputs describing the high speed shaft, when present
Length of the high speed shaft
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 10.0
Diameter of the high speed shaft at beginning (generator) and end (generator) points
No Additional ItemsEach item of this array must be:
Units: m
Thickness of the high speed shaft at beginning (generator) and end (generator) points
No Additional ItemsEach item of this array must be:
Units: m
Material name identifier
Inputs describing the nose/turret at beginning (bedplate) and end (main bearing) points
Diameter of the nose/turret at beginning (bedplate) and end (main bearing) points
No Additional ItemsEach item of this array must be:
Units: m
Thickness of the nose/turret at beginning (bedplate) and end (main bearing) points
No Additional ItemsEach item of this array must be:
Units: m
Inputs describing the hollow elliptical bedplate used in direct drive configurations
Thickness of the hollow elliptical bedplate used in direct drive configurations
Bedplate I-beam flange width used in geared configurations
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 3.0
Bedplate I-beam flange thickness used in geared configurations
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 1.0
Bedplate I-beam web thickness used in geared configurations
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 1.0
Material name identifier
Inputs describing all other drivetrain components, the assembly of brake, hvac, converter, transformer, and main bearings
Override regular regression-based calculation of brake mass with this value
Units: kg
Value must be greater or equal to 0.0
Regression-based scaling coefficient on machine rating to get HVAC system mass
Units: kg/kW
Value must be greater or equal to 0.0
Override regular regression-based calculation of converter mass with this value
Units: kg
Value must be greater or equal to 0.0
Override regular regression-based calculation of transformer mass with this value
Units: kg
Value must be greater or equal to 0.0
Type of bearing for first main bearing
Must be one of:
- "CARB"
- "CRB"
- "SRB"
- "TRB"
Type of bearing for second main bearing
Must be one of:
- "CARB"
- "CRB"
- "SRB"
- "TRB"
If power electronics are located uptower (True) or at tower base (False)
Rigid body modeling the assembly of brake, hvac, converter, transformer, and main bearings. Their inertia is defined with respect to the tower top coordinate system.
Same definition as elastic_propertiesLength of generator along the shaft
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
User input override of generator radius, only used when using simple generator scaling
Units: m
Value must be greater or equal to 0.0 and lesser or equal to 20.0
User input override of generator mass, only used when using simple generator mass scaling
Units: kg
Value must be greater or equal to 0.0 and lesser or equal to 1000000000.0
User input override of generator rpm-efficiency values, with rpm as grid input and eff as values input
Rigid body modeling the generator. The properties are defined in the generator coordinate system, which is centered at the center of the generator, and has x aligned along the shaft pointing downwind, y parallel to the ground, and z pointing upwards (tilted, if tilt is present). The rotational inertia of the generator is around the x axis.
Same definition as elastic_propertiesRigid body modeling the overall drivetrain, excluding hub and yaw systems. The properties are defined in the tower-top coordinate system, which is centered at the center of the tower top, and has x aligned along the prevailing wind direction, y parallel to the ground, and z pointing upwards.
Same definition as elastic_propertiesData describing the yaw system located at tower top.
Rigid body modeling the yaw system. The properties are defined in the tower-top coordinate system, which is centered at the center of the tower top, and has x aligned along the prevailing wind direction, y parallel to the ground, and z pointing upwards.
Same definition as elastic_propertiesData describing the wind turbine tower.
The aerodynamic, structural, and elastic characteristics of the wind turbine tower are defined at a common reference axis. The axis is defined with sets of x, y, and z points. The reference system for x, y, and z is located at tower base for land-based turbines and at the mean sea level for offshore turbines. x is parallel to the ground pointing downwind, y is parallel to the ground and to the rotor plane, and z is perpendicular to the ground pointing upwards. Standard towers are only defined along z. Total tower length is computed by integrating the fields x, y, and z three-dimensionally.
Outer diameters of the tower defined from base (grid = 0) to top (grid = 1).
Multiplier of tower mass to account for the mass of the auxiliary systems, such as stairs, elevator, paint, or extra structural elements. This can be used to convert the mass of the steel cylinders to the total mass of the monopile.
Units: dimensionless
Value must be greater or equal to 1.0 and lesser or equal to 2.0
...
No Additional ItemsEach item of this array must be:
structural component identifier
material identifier
thickness of the laminate
The equivalent elastic properties of a beam are defined in elastic_properties. Here, 6x6 stiffness and mass matrices are defined. Out of 36 entries of the matrices, given the symmetry, the yaml file requires the definition of only 21 values as inputs for the stiffness matrix, whereas the inertia matrix is defined in terms of unit mass, coordinates of the center of mass, and mass moments of inertia. For the blade, these properties are defined with respect to the aerodynamic twist, which is the same as structural twist.
Total mass of transition piece
Units: kg
Value must be greater or equal to 0.0
Total cost of transition piece
Units: USD
Value must be greater or equal to 0.0
Total mass of gravity foundation addition onto monopile
Units: kg
Value must be greater or equal to 0.0
The hydrodynamic, structural, and elastic characteristics of the wind turbine monopile are defined at a common reference axis. The axis is defined with sets of x, y, and z points. The reference system for x, y, and z is located at the mean sea level. x is parallel to the sea level pointing downwind, y is parallel to the sea level and to the rotor plane, and z is perpendicular to the sea level pointing upwards. Standard monopiles are only defined along z. Total monopile length is computed by integrating the fields x, y, and z three-dimensionally.
Outer diameters of the monopile defined from base (grid = 0) to top (grid = 1).
Added mass coefficient for the monopile defined in terms of grid and values that default to 1.
No Additional Items
Each item of this array must be:
Units: dimensionless
Drag coefficient for the monopile
Multiplier of monopile mass to account for the mass of the auxiliary systems, such as paint or extra structural elements. This can be used to convert the mass of the steel cylinders to the total mass of the monopile.
Units: dimensionless
Value must be greater or equal to 1.0 and lesser or equal to 2.0
...
No Additional ItemsEach item of this array must be:
structural component identifier
material identifier
thickness of the laminate
The equivalent elastic properties of a beam are defined in elastic_properties. Here, 6x6 stiffness and mass matrices are defined. Out of 36 entries of the matrices, given the symmetry, the yaml file requires the definition of only 21 values as inputs for the stiffness matrix, whereas the inertia matrix is defined in terms of unit mass, coordinates of the center of mass, and mass moments of inertia. For the blade, these properties are defined with respect to the aerodynamic twist, which is the same as structural twist.
Total mass of transition piece
Units: kg
Value must be greater or equal to 0.0
Total cost of transition piece
Units: USD
Value must be greater or equal to 0.0
Total mass of gravity foundation addition onto monopile
Units: kg
Value must be greater or equal to 0.0
Material of jacket members
Number of bays (x-joints) in the vertical direction for jackets.
Number of legs for jacket.
Radius of foot (bottom) of jacket, in meters.
Radius of head (top) of jacket, in meters.
Overall jacket height, meters.
Leg thickness, meters. Constant throughout each leg.
Mud brace included if true.
Leg diameter, meters. Constant throughout each leg.
The floating platform ontology uses a graph-like representation of the geometry with Joints and Members. Additional rigid body point masses can be defined at the joints as well.
Joints are the nodes of the graph representation of the floating platform. They must be assigned a unique name for later reference by the members.
No Additional ItemsEach item of this array must be:
Unique name of the joint (node)
Coordinates (x,y,z or r,θ,z) of the joint in the global coordinate system.
No Additional ItemsEach item of this array must be:
Units: m
Whether the transition piece and turbine tower attach at this node
Whether to use cylindrical coordinates (r,θ,z), with (r,θ) lying in the x/y-plane, instead of Cartesian coordinates.
If this joint is compliant is certain DOFs, then specify which are compliant (True) in the member/element coordinate system). If not specified, default is all entries are False (completely rigid). For instance, a ball joint would be Rx=Ry=Rz=False, Rxx=Ryy=Rzz=True
Euler angles [alpha, beta, gamma] that describe the rotation of the Reaction coordinate system relative to the global coordinate system α is a rotation around the z axis, β is a rotation around the x' axis, γ is a rotation around the z" axis.
No Additional ItemsEach item of this array must be:
No Additional Items
Each item of this array must be:
Name of the member
Name of joint/node connection
Name of joint/node connection
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- outer_diameter
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- side_lengths_a
- side_lengths_b
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- side_lengths1
- side_lengths2
Specifies cross-sectional shape of the member. If circular, then the outerdiameter field is required. If polygonal, then the sidelengths, angles, and rotation fields are required
Must be one of:
- "circular"
- "rectangular"
- "polygonal"
Gridded values describing diameter at non-dimensional axis from joint1 to joint2
Gridded values describing side length a for rectangular members at non-dimensional axis from joint1 to joint2
Gridded values describing side length b for rectangular members at non-dimensional axis from joint1 to joint2
Polygon side lengths at joint1
No Additional ItemsEach item of this array must be:
Units: m
Value must be greater or equal to 0
Polygon side lengths at joint1
No Additional ItemsEach item of this array must be:
Units: m
Value must be greater or equal to 0
Polygon angles with the ordering such that angle[i] is between sidelength[i] and sidelength[i+1]
No Additional ItemsEach item of this array must be:
Units: deg
Value must be greater or equal to 0
Angle between principle axes of the cross-section and the member coordinate system. Essentially the rotation of the member if both joints were placed on the global x-y axis with the first side length along the z-axis
Units: deg
Scaling factor for the member mass to account for auxiliary structures, such as elevator, ladders, cables, platforms, fasteners, etc
Units: dimensionless
Value must be greater or equal to 1.0
Material layer properties
No Additional ItemsEach item of this array must be:
structural component identifier
material identifier
Gridded values describing thickness along non-dimensional axis from joint1 to joint2
material identifier
Units: m
Value must be greater or equal to 0
Units: m
Value must be greater or equal to 0
Units: m
Value must be greater or equal to 0
Units: m
Value must be greater or equal to 0
Spacing between stiffeners in non-dimensional grid coordinates. Value of 0.0 means no stiffeners
Units: dimensionless
Value must be greater or equal to 0.0 and lesser or equal to 1.0
material identifier
Units: m
Value must be greater or equal to 0
Units: m
Value must be greater or equal to 0
Units: m
Value must be greater or equal to 0
Units: m
Value must be greater or equal to 0
Spacing between stiffeners in angle (deg). Value of 0.0 means no stiffeners
Units: deg
Value must be greater or equal to 0.0 and lesser or equal to 360
material identifier
thickness of the bulkhead at non-dimensional locations of the member [0..1]
Different types of permanent and/or variable ballast
No Additional ItemsEach item of this array must be:
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- material
- volume
If true, then this ballast is variable and adjusted by control system. If false, then considered permanent
material identifier
Total volume of ballast (permanent ballast only)
Units: m^3
Value must be greater or equal to 0
Flag that defines whether a floater member is flooded or not.
Additional joints that are defined along the non-dimensional member axis can be defined here. Unlike the joints defined in the global coordinate system in the joints section of the ontology, these joints will change their absolute (x,y,z) location if the member diameter is altered the or joint1 or joint2 locations are changed during an optimization. This is especially useful when designing a truss-like structure with pontoons attaching to primary members or columns in a semisubmersible. Like the joints above, these must be given a unique name.
Each item of this array must be:
User-defined added mass coefficient if axi-symmetric or user-defined added mass coefficient in x-direction
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Value must be greater or equal to -1.0
User-defined added mass coefficient in y-direction
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Value must be greater or equal to -1.0
User-defined pressure coefficient
User-defined drag coefficient if axi-symmetric or user-defined drag coefficient in x-direction
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Value must be greater or equal to -1.0
User-defined drag coefficient in y-direction
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Value must be greater or equal to -1.0
Additional point masses at joints with user-customized properties
No Additional ItemsEach item of this array must be:
Name of joint/node connection
Mass of this rigid body
Units: kg
Value must be greater or equal to 0
Cost of this rigid body
Units: USD
Value must be greater or equal to 0
Offset from joint location to center of mass (CM) of body in dx, dy, dz
No Additional ItemsEach item of this array must be:
Units: m
Moments of inertia around body CM in Ixx, Iyy, Izz
No Additional ItemsEach item of this array must be:
Units: kg*m^2
Value must be greater or equal to 0
User-defined added mass coefficient if axi-symmetric or user-defined added mass coefficient in x-direction
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Value must be greater or equal to -1.0
User-defined pressure coefficient
User-defined drag coefficient if axi-symmetric or user-defined drag coefficient in x-direction
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Value must be greater or equal to -1.0
Total mass of transition piece
Units: kg
Value must be greater or equal to 0.0
Total cost of transition piece
Units: USD
Value must be greater or equal to 0.0
The mooring system ontology follows closely the input file format for MoorDyn or MAP++. Additional information can be found in the MoorDyn user guide <http://www.matt-hall.ca/files/MoorDyn-Users-Guide-2017-08-16.pdf>_ .
List of nodes in the mooring system
No Additional ItemsEach item of this array must be:
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- anchor_type
- joint
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- fairlead_type
- joint
The following properties are required:
- location
Name or ID of this node for use in line segment
Must be one of:
- "fixed"
- "fix"
- "connection"
- "connect"
- "free"
- "vessel"
– Coordinates x, y, and z of the connection (relative to inertial reference frame if Fixed or Connect, relative to platform reference frame if Vessel). In the case of Connect nodes, it is simply an initial guess for position before MoorDyn calculates the equilibrium initial position.
No Additional ItemsEach item of this array must be:
Units: m
For anchor positions and fairlead attachments, reference a joint name from the "joints" section or an "axial_joint" on a member
Name of anchor type from anchor_type list
Must be one of:
- "rigid"
- "actuated"
- "ball"
Clump weight mass
Units: kg
Value must be greater or equal to 0.0
Floater volume
Units: m^3
Value must be greater or equal to 0.0
Product of drag coefficient and projected area (assumed constant in all directions) to calculate a drag force for the node
Units: m^2
Value must be greater or equal to 0.0
Added mass coefficient used along with node volume to calculate added mass on node
List of all mooring line properties in the mooring system
No Additional ItemsEach item of this array must be:
List of mooring line properties used in the system
No Additional ItemsEach item of this array must be:
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- mass_density
- stiffness
- breaking_load
- cost
Name of material or line type to be referenced by line segments
the volume-equivalent diameter of the line – the diameter of a cylinder having the same displacement per unit length
Units: m
Value must be greater or equal to 0.0
Type of material for property lookup
Must be one of:
- "chain"
- "chain_stud"
- "nylon"
- "polyester"
- "polypropylene"
- "wire_fiber"
- "fiber"
- "wire"
- "wire_wire"
- "iwrc"
- "Chain"
- "Chain_Stud"
- "Nylon"
- "Polyester"
- "Polypropylene"
- "Wire"
- "Wire_Fiber"
- "Fiber"
- "Wire_Wire"
- "IWRC"
- "CHAIN"
- "CHAIN_STUD"
- "NYLON"
- "POLYESTER"
- "POLYPROPYLENE"
- "WIRE"
- "WIRE_FIBER"
- "FIBER"
- "IRE_WIRE"
- "custom"
- "Custom"
- "CUSTOM"
mass per unit length (in air)
Units: kg/m
Value must be greater or equal to 0.0
axial line stiffness, product of elasticity modulus and cross-sectional area
Units: N
Value must be greater or equal to 0.0
cost per unit length
Units: USD/m
Value must be greater or equal to 0.0
line break tension
Units: N
Value must be greater or equal to 0.0
internal damping (BA)
Units: N*s
transverse added mass coefficient (with respect to line displacement)
Value must be greater or equal to 0.0
tangential added mass coefficient (with respect to line displacement)
Value must be greater or equal to 0.0
transverse drag coefficient (with respect to frontal area, d*l)
Value must be greater or equal to 0.0
tangential drag coefficient (with respect to surface area, πdl)
Value must be greater or equal to 0.0
List of anchor properties used in the system
No Additional ItemsEach item of this array must be:
If the conditions in the "If" tab are respected, then the conditions in the "Then" tab should be respected. Otherwise, the conditions in the "Else" tab should be respected.
The following properties are required:
- mass
- cost
- max_lateral_load
- max_vertical_load
Name of anchor to be referenced by anchor_id in Nodes section
Type of anchor for property lookup
Must be one of:
- "drag_embedment"
- "suction"
- "plate"
- "micropile"
- "sepla"
- "Drag_Embedment"
- "Suction"
- "Plate"
- "Micropile"
- "Sepla"
- "DRAG_EMBEDMENT"
- "SUCTION"
- "PLATE"
- "MICROPILE"
- "SEPLA"
- "custom"
- "Custom"
- "CUSTOM"
mass of the anchor
Units: kg
Value must be greater or equal to 0.0
cost of the anchor
Units: USD
Value must be greater or equal to 0.0
Maximum lateral load (parallel to the sea floor) that the anchor can support
Units: N
Value must be greater or equal to 0.0
Maximum vertical load (perpendicular to the sea floor) that the anchor can support
Units: N
Value must be greater or equal to 0.0
Database of airfoils. windIO describes the airfoils in terms of coordinates, polars, and unsteady aerodynamic coefficients. The yaml entry airfoils consists of a list of elements. For each set of coordinates, multiple sets of polars and parameters can co-exist. Note that the airfoils listed in this database are not all necessarily used in the blade. Only the ones called in airfoils' withinouter_shapeof thecomponentblade` will actually be loaded to model the blade.
Each item of this array must be:
Name of the airfoil
Text documenting airfoil data
The airfoil coordinates are specified here in the sub-fields x and y. x and y must have the same length. x must be defined between 0, which corresponds to the leading edge, and 1, which corresponds to the trailing edge. Airfoil coordinates should be defined from trailing edge (x=1) towards the suction side (mostly positive y values), to leading edge (x=0, y=0), to the pressure side (mostly negative y), and conclude at the trailing edge pressure side (x=1). Flatback airfoils can be defined either open (x=1, y!=0) or closed (x=1, y=0).
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to 0.0 and lesser or equal to 1.0
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to -1.0 and lesser or equal to 1.0
Float defined between 0 (plate) and 1 (cylinder) to specify the relative thickness of the airfoil. This generates a small redundancy (airfoil thickness could be determined from the field coordinates), but it simplifies the converters.
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 1
Float defined between 0 (leading edge) and 1 (trailing edge) to specify the chordwise coordinate of the aerodynamic center used to define the polars.
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 1
Different sets of polars at varying conditions.
No Additional ItemsEach item of this array must be:
Tag to identify the set polars that can be called in blade
Text to identify the setup for the definition of the polars
Sets of polars at varying Reynolds. For each set, Reynolds number, lift, drag, and moment coefficients must be provided. Optionally, unsteady aerodynamic coefficients can be listed.
No Additional ItemsEach item of this array must be:
Reynolds number of the polars
Value must be greater or equal to 0
Lift coefficient as a function of angle of attack (deg)
Grid of angles of attack to describe polars
No Additional ItemsEach item of this array must be:
Units: deg
Value must be greater or equal to -180 and lesser or equal to 180
Lift, drag and moment coefficients
No Additional ItemsEach item of this array must be:
Units: dimensionless
Drag coefficient as a function of angle of attack (deg)
Grid of angles of attack to describe polars
Same definition as gridMoment coefficient as a function of angle of attack (deg)
Grid of angles of attack to describe polars
Same definition as grid0-lift angle of attack
Units: deg
Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0
Units: deg
Angle of attack at f=0.7, (approximately the stall angle) for AOA
Units: deg
Recovery factor in the range [0.85 - 0.95]
Slope of the 2D normal force coefficient curve
Units: 1/rad
Value must be greater or equal to 0.0
Initial value of the time constant associated with Df in the expression of Df and f. [default = 3]
Value must be greater or equal to 0.0
Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on Re,M, and airfoil class. [default = 6]
Value must be greater or equal to 0.0
Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental data. [default = 1.7]
Value must be greater or equal to 0.0
Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13, default = 11]
Value must be greater or equal to 6.0 and lesser or equal to 13.0
Constant in the expression of phialpha^c and phiq^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.14]
Constant in the expression of phialpha^c and phiq^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.53]
Constant in the expression of phialpha^c and phiq^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.3]
Constant in the expression of phialpha^c and phiq^c. This value is relatively insensitive for thin airfoils, but may be different for turbine airfoils. [from experimental results, defaults to 0.7]
Constant in the expression of K'''q,cmq^nc, and k_m,q. [from experimental results, defaults to 1]
Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil.
Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil.
Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil.
Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil.
Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers.
As Cn1 for negative AOAs
Strouhal's shedding frequency constant. [default = 0.19]
2D drag coefficient value at 0-lift.
2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up.
Constant in the \hat(x)cp curve best-fit; = (\hat(x)AC-0.25).
Constant in the \hat(x)_cp curve best-fit.
Constant in the \hat(x)_cp curve best-fit.
Constant in the \hat(x)_cp curve best-fit.
Constant in the expression of Cc due to leading edge vortex effects.
Constant in the expression of \hat(x)_cp^v. [default = 0.2]
Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees]
Units: deg
Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20]
Units: Hz
Database of the materials. The schema enforces that the fields name, orth, rho, E, and nu are specified. For composites, direction 1 is aligned with the main fiber direction, direction 2 is in the plane transverse to the fibers, and direction 3 is perspendicular to the laminate plane. Note that fiber angles are specified in structure of the component blade.
Each item of this array must be:
Name of the material
Optional string to describe the origin of the material, for example referencing a report or a paper
Optional field describing where the data come from
Flag specifying whether a material is isotropic (0) or orthotropic (1). This determines whether some of the fields below are specified as a float or an array of floats.
Density of the material. For composites, this is the density of the laminate once cured.
Units: kg/m^3
Value must be greater or equal to 0 and lesser or equal to 20000
Stiffness modulus. For orthotropic materials, it consists of an array with E11, E22, and E33.
Units: Pa
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: Pa
Value must be greater or equal to 0
Shear stiffness modulus. For orthotropic materials, it consists of an array with G12, G13, and G23.
Units: Pa
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: Pa
Value must be greater or equal to 0
Poisson ratio. For orthotropic materials, it consists of an array with nu12, nu13 and nu23. For isotropic materials, a minimum of -1 and a maximum of 0.5 are imposed. No limits are imposed to anisotropic materials.
Units: dimensionless
Value must be greater or equal to -1.0 and lesser or equal to 0.5
No Additional Items
Each item of this array must be:
Units: dimensionless
Thermal coefficient of expansion. For orthotropic materials, it consists of an array with alpha11, alpha22, and alpha33.
Units: 1/K
No Additional Items
Each item of this array must be:
Units: 1/K
Ultimate tensile strength. For orthotropic materials, it consists of an array with Xt11, Xt22, and Xt33.
Units: Pa
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: Pa
Value must be greater or equal to 0
Ultimate compressive strength. For orthotropic materials, it consists of an array with Xc11, Xc22, and Xc33. Values are defined positive.
Units: Pa
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: Pa
Value must be greater or equal to 0
Ultimate yield strength for metals. For orthotropic materials, it consists of an array with the strength in directions 12, 13 and 23
Units: Pa
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: Pa
Value must be greater or equal to 0
Ultimate shear strength. For orthotropic materials, it consists of an array with the strength in directions 12, 13 and 23. Values are defined positive.
Units: Pa
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: Pa
Value must be greater or equal to 0
Ply thickness of a composite material. The unit of measure is m. The actual laminate thickness is defined in the fields components.
Units: m
Value must be greater or equal to 0 and lesser or equal to 0.1
Unit cost of the material. For composites, this is the unit cost of the dry fabric.
Units: USD/kg
Value must be greater or equal to 0 and lesser or equal to 1000
Fiber volume fraction of a composite material. The minimum values is 0 (only matrix), the maximum value is 1 (only fibers).
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 1
Fiber weight fraction of a composite material. The minimum values is 0 (only matrix), the maximum value is 1 (only fibers).
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 1
Density of the fibers of a composite material. Standard glass fiber has a fiber density of approximately 2600 kg/m3, while standard carbon fiber has a fiber density of approximately 1800 kg/m3.
Units: kg/m^3
Value must be greater or equal to 0 and lesser or equal to 10000
Aerial density of a fabric of a composite material.
Units: kg/m^2
Value must be greater or equal to 0 and lesser or equal to 10000
Flag to define the manufacturing process behind the laminate, for example 0 - coating, 1 - sandwich filler , 2 - shell skin, 3 - shear webs, 4 - spar caps, 5 - TE reinf.
Units: dimensionless
Must be one of:
- 0
- 1
- 2
- 3
- 4
- 5
Fraction of material that ends up wasted during manufacturing.
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 1
Mass of a fabric roll.
Units: kg
Value must be greater or equal to 0 and lesser or equal to 10000
Mode 1 critical energy-release rate.
Units: J/m^2
Mode 2 critical energy-release rate.
Units: J/m^2
Fracture angle under pure transverse compression.
Units: deg
Fatigue S/N curve fitting parameter S=A*N^(-1/m). An array can be defined as a function of R (for composites) or as a function of number of cycles N (for multi-segment S-N curves, such as for metals).
Units: dimensionless
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to 0
Fatigue S/N curve fitting parameter S=A*N^(-1/m). An array can be defined as a function of R (for composites) or as a function of number of cycles N (for multi-segment S-N curves, such as for metals).
Units: dimensionless
Value must be greater or equal to 0
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 1000
Fatigue stress ratio. An array can be defined to build Goodman-correction diagrams.
Units: dimensionless
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to -100 and lesser or equal to 100
Number of cycles for fatigue failure. An array can be defined to support multi-segment S-N curves such as for metals.
Units: dimensionless
No Additional Items
Each item of this array must be:
Units: dimensionless
Value must be greater or equal to 1 and lesser or equal to 1e+10
Dictionary reporting the data describing the wind turbine controller
Cut-in wind speed of the wind turbine.
Units: m/s
Value must be greater or equal to 0 and lesser or equal to 10
Cut-out wind speed of the wind turbine.
Units: m/s
Value must be greater or equal to 0 and lesser or equal to 50
Maximum allowable blade tip speed.
Units: m/s
Value must be greater or equal to 60 and lesser or equal to 120
Minimum pitch angle, where the default is 0 deg
Units: deg
Value must be greater or equal to -10.0 and lesser or equal to 90.0
Maximum pitch angle, where the default is 90 deg
Units: deg
Value must be greater or equal to 10.0 and lesser or equal to 120.0
Maximum pitch rate of the rotor blades.
Units: deg/s
Value must be greater or equal to 0 and lesser or equal to 30.0
Nondimensional factor shaving peak thrust. 1 means no peak thrust shaving
Value must be greater or equal to 0 and lesser or equal to 1.0
Maximum torque rate of the wind turbine generator.
Units: N*m/s
Value must be greater or equal to 1000 and lesser or equal to 100000000
Rated tip speed ratio of the wind turbine. As default, it is maintained constant in region II.
Units: dimensionless
Value must be greater or equal to 0 and lesser or equal to 15
Minimum rotor speed.
Units: rpm
Value must be greater or equal to 0 and lesser or equal to 20.0
Maximum rotor speed.
Units: rpm
Value must be greater or equal to 0
Modal response and loads and performance metrics describing the turbine
Name and version of the numerical solver used to generate the outputs
Data points where outputs are computed at varying wind speed, rotor speed, etc.
No Additional ItemsEach item of this array must be:
Average wind speed measured at hub height corresponding to the outputs
Units: m/s
Value must be greater or equal to 0.0 and lesser or equal to 200.0
Rotor speed corresponding to the outputs
Units: rpm
Value must be greater or equal to 0.0 and lesser or equal to 200.0
Collective blade pitch angle corresponding to the outputs
Units: deg
Value must be greater or equal to 0.0 and lesser or equal to 90.0
Rotor tip speed ratio corresponding to the outputs
Value must be greater or equal to 0.0 and lesser or equal to 50.0
Outputs integrated along blade span
Mechanical power of the rotor measured at the high speed shaft
Units: W
Eelectrical power of the rotor measured at the output of the generator
Units: W
Electrical torque of the generator
Units: N*m
Aerodynamic thrust of the rotor measured at the hub
Units: N
Mechanical torque of the rotor measured at the hub
Units: N*m
Outputs distributed along blade span
Aerodynamic loading along the axial rotor direction
Loading described along a beam, expressed in N per meter
No Additional ItemsEach item of this array must be:
Units: N/m
Aerodynamic loading along the tangential rotor direction
Loading described along a beam, expressed in N per meter
Same definition as valuesBlade deflection with respect to the undeflected configuration along the x axis for the pitching blade root coordinate system
Blade deflection with respect to the undeflected configuration along the y axis for the pitching blade root coordinate system
Blade deflection with respect to the undeflected configuration along the z axis for the pitching blade root coordinate system
Blade rotation with respect to the undeflected configuration along the z axis for the pitching blade root coordinate system
Distribution along blade span of the reaction force along the x axis (edgewise shear). The force follows the pitching blade root coordinate system
Loading described along a beam, expressed in N per meter
Same definition as valuesDistribution along blade span of the reaction force along the y axis (flapwise shear). The force follows the pitching blade root coordinate system
Loading described along a beam, expressed in N per meter
Same definition as valuesDistribution along blade span of the reaction force along the z axis (axial). The force follows the pitching blade root coordinate system
Loading described along a beam, expressed in N per meter
Same definition as valuesDistribution along blade span of the reaction moment along the x axis (flapwise moment). The moment follows the pitching blade root coordinate system
Loading described along a beam, expressed in N m per meter
No Additional ItemsEach item of this array must be:
Units: N/m
Distribution along blade span of the reaction moment along the y axis (edgewise moment). The moment follows the pitching blade root coordinate system
Loading described along a beam, expressed in N m per meter
Same definition as valuesDistribution along blade span of the reaction moment along the z axis (torsional moment). The moment follows the pitching blade root coordinate system
Loading described along a beam, expressed in N m per meter
Same definition as valuesUndamped natural frequencies of the system
No Additional ItemsEach item of this array must be:
Units: Hz
Value must be greater or equal to 0.0
Critical damping ratios of the modes characterizing the system
No Additional ItemsEach item of this array must be:
Value must be greater or equal to 0.0
Text field to describe the wind turbine, the changes to previous versions, etc,