def __init__(
self,
xyz_le: np.ndarray = np.array([0, 0, 0]),
chord: float = 1.,
twist_angle: float = 0,
twist_axis: np.ndarray = np.array([0, 1, 0]),
airfoil: Airfoil = Airfoil("naca0012"),
control_surface_is_symmetric: bool = True,
control_surface_hinge_point: float = 0.75,
control_surface_deflection: float = 0.,
):
"""
Initialize a new wing cross section.
Args:
xyz_le: xyz-coordinates of the leading edge of the cross section, relative to the wing's datum.
chord: Chord of the wing at this cross section
twist_angle: Twist angle, in degrees, as defined about the leading edge.
twist_axis: The twist axis vector, used if twist_angle != 0.
airfoil: Airfoil associated with this cross section. [aerosandbox.Airfoil]
control_surface_is_symmetric: Is the control surface symmetric? (e.g. True for flaps, False for ailerons.)
control_surface_hinge_point: The location of the control surface hinge, as a fraction of chord.
control_surface_deflection: Control deflection, in degrees. Downwards-positive.
"""
self.xyz_le = xyz_le
self.chord = chord
self.twist = twist_angle
self.twist_axis = twist_axis
self.airfoil = airfoil
self.control_surface_is_symmetric = control_surface_is_symmetric
self.control_surface_hinge_point = control_surface_hinge_point
self.control_surface_deflection = control_surface_deflection
def __init__(self,
xyz_le: np.ndarray = np.array([0, 0, 0]),
chord: float = 1.,
twist: float = 0,
twist_angle=None, # TODO Deprecate
airfoil: Airfoil = Airfoil("naca0012"),
control_surface_is_symmetric: bool = True,
control_surface_hinge_point: float = 0.75,
control_surface_deflection: float = 0.,
):
"""
Initialize a new wing cross section.
Args:
xyz_le: xyz-coordinates of the leading edge of the cross section, relative to the wing's datum.
chord: Chord of the wing at this cross section
twist: Twist angle, in degrees, as defined about the leading edge.
The twist axis is computed with the following procedure:
* The quarter-chord point of this WingXSec and the following one are identified.
* A line is drawn connecting them, and it is converted into a direction vector.
* That direction vector is projected onto the Y-Z plane.
* That direction vector is now the twist axis.
airfoil: Airfoil associated with this cross section. [aerosandbox.Airfoil]
control_surface_is_symmetric: Is the control surface symmetric? (e.g. True for flaps, False for ailerons.)
control_surface_hinge_point: The location of the control surface hinge, as a fraction of chord.
control_surface_deflection: Control deflection, in degrees. Downwards-positive.
"""
if twist_angle is not None:
import warnings
warnings.warn("DEPRECATED: 'twist_angle' has been renamed 'twist', and will break in future versions.")
twist = twist_angle
self.xyz_le = np.array(xyz_le)
self.chord = chord
self.twist = twist
self.airfoil = airfoil
self.control_surface_is_symmetric = control_surface_is_symmetric
self.control_surface_hinge_point = control_surface_hinge_point
self.control_surface_deflection = control_surface_deflection
def diamond_airfoil(
t_over_c: float,
n_points_per_panel=2,
) -> Airfoil:
x_nondim = [1, 0.5, 0, 0.5, 1]
y_nondim = [0, 1, 0, -1, 0]
x = np.concatenate([
list(np.cosspace(a, b, n_points_per_panel))[:-1]
for a, b in zip(x_nondim[:-1], x_nondim[1:])
] + [[x_nondim[-1]]])
y = np.concatenate([
list(np.cosspace(a, b, n_points_per_panel))[:-1]
for a, b in zip(y_nondim[:-1], y_nondim[1:])
] + [[y_nondim[-1]]])
y = y * t_over_c
coordinates = np.array([x, y]).T
return Airfoil(
name="Diamond",
coordinates=coordinates,
)
def __init__(
self,
xyz_le: Union[np.ndarray, List] = np.array([0, 0, 0]),
chord: float = 1.,
twist: float = 0,
airfoil: Airfoil = None,
control_surfaces: Optional[List['ControlSurface']] = None,
analysis_specific_options: Optional[Dict[type, Dict[str, Any]]] = None,
**deprecated_kwargs,
):
"""
Defines a new wing cross section.
Args:
xyz_le: An array-like that represents the xyz-coordinates of the leading edge of the cross section, in
geometry axes.
chord: Chord of the wing at this cross section.
twist: Twist angle, in degrees, as defined about the leading edge.
The twist axis is computed with the following procedure:
* The quarter-chord point of this WingXSec and the following one are identified.
* A line is drawn connecting them, and it is normalized to a unit direction vector.
* That direction vector is projected onto the geometry Y-Z plane.
* That direction vector is now the twist axis.
airfoil: Airfoil associated with this cross section. [aerosandbox.Airfoil]
control_surfaces: A list of control surfaces in the form of ControlSurface objects.
analysis_specific_options: Analysis-specific options are additional constants or modeling assumptions
that should be passed on to specific analyses and associated with this specific geometry object.
This should be a dictionary where:
* Keys are specific analysis types (typically a subclass of asb.ExplicitAnalysis or
asb.ImplicitAnalysis), but if you decide to write your own analysis and want to make this key
something else (like a string), that's totally fine - it's just a unique identifier for the
specific analysis you're running.
* Values are a dictionary of key:value pairs, where:
* Keys are strings.
* Values are some value you want to assign.
This is more easily demonstrated / understood with an example:
>>> analysis_specific_options = {
>>> asb.AeroBuildup: dict(
>>> include_wave_drag=True,
>>> )
>>> }
Note: Control surface definition through WingXSec properties (control_surface_is_symmetric, control_surface_hinge_point, control_surface_deflection)
is deprecated. Control surfaces should be handled according to the following protocol:
1. If control_surfaces is an empty list (default, user does not specify any control surfaces), use deprecated WingXSec control surface definition properties.
This will result in 1 control surface at this xsec.
Usage example:
>>> xsecs = asb.WingXSec(
>>> chord = 2
>>> )
2. If control_surfaces is a list of ControlSurface instances, use ControlSurface properties to define control surfaces. This will result in as many
control surfaces at this xsec as there are entries in the control_surfaces list (an arbitrary number >= 1).
Usage example:
>>>xsecs = asb.WingXSec(
>>> chord = 2,
>>> control_surfaces = [
>>> ControlSurface(
>>> trailing_edge = False
>>> )
>>> ]
>>>)
3. If control_surfaces is None, override deprecated control surface definition properties and do not define a control surface at this xsec. This will
result in 0 control surfaces at this xsec.
Usage example:
>>>xsecs = asb.WingXSec(
>>> chord = 2,
>>> control_surfaces = None
>>>)
See avl.py for example of control_surface handling using this protocol.
"""
### Set defaults
if airfoil is None:
airfoil = Airfoil("naca0012")
if control_surfaces is None:
control_surfaces = []
if analysis_specific_options is None:
analysis_specific_options = {}
self.xyz_le = np.array(xyz_le)
self.chord = chord
self.twist = twist
self.airfoil = airfoil
self.control_surfaces = control_surfaces
self.analysis_specific_options = analysis_specific_options
### Handle deprecated arguments
if 'twist_angle' in locals():
import warnings
warnings.warn(
"DEPRECATED: 'twist_angle' has been renamed 'twist', and will break in future versions.",
stacklevel=2)
self.twist = twist_angle
if ('control_surface_is_symmetric' in locals()
or 'control_surface_hinge_point' in locals()
or 'control_surface_deflection' in locals()):
import warnings
warnings.warn(
"DEPRECATED: Define control surfaces using the `control_surfaces` parameter, which takes in a list of asb.ControlSurface objects.",
stacklevel=2)
if 'control_surface_is_symmetric' not in locals():
control_surface_is_symmetric = True
if 'control_surface_hinge_point' not in locals():
control_surface_hinge_point = 0.75
if 'control_surface_deflection' not in locals():
control_surface_deflection = 0
self.control_surfaces.append(
ControlSurface(
hinge_point=control_surface_hinge_point,
symmetric=control_surface_is_symmetric,
deflection=control_surface_deflection,
))
analysis_specific_options = {}
self.name = name
self.trailing_edge = trailing_edge
self.hinge_point = hinge_point
self.symmetric = symmetric
self.deflection = deflection
self.analysis_specific_options = analysis_specific_options
if __name__ == '__main__':
wing = Wing(xsecs=[
WingXSec(
xyz_le=[0, 0, 0],
chord=1,
airfoil=Airfoil("naca0012"),
twist=0,
),
WingXSec(
xyz_le=[0.5, 1, 0],
chord=0.5,
airfoil=Airfoil("naca0012"),
twist=0,
),
WingXSec(
xyz_le=[0.7, 1, 0.3],
chord=0.3,
airfoil=Airfoil("naca0012"),
twist=0,
)
]).translate([1, 0, 0])
y = y * t_over_c
coordinates = np.array([x, y]).T
return Airfoil(
name="Diamond",
coordinates=coordinates,
)
generic_cambered_airfoil = Airfoil(
name="Generic Cambered Airfoil",
CL_function=lambda alpha, Re, mach, deflection, :
( # Lift coefficient function
(alpha * np.pi / 180) * (2 * np.pi) + 0.4550),
CD_function=lambda alpha, Re, mach, deflection:
( # Profile drag coefficient function
(1 + (alpha / 5)**2) * 2 * Cf_flat_plate(Re_L=Re)),
CM_function=lambda alpha, Re, mach, deflection:
( # Moment coefficient function about quarter-chord
-0.1),
coordinates=get_UIUC_coordinates(name="clarky"))
generic_airfoil = Airfoil(
name="Generic Airfoil",
CL_function=lambda alpha, Re, mach, deflection, :
( # Lift coefficient function
(alpha * np.pi / 180) * (2 * np.pi)),
CD_function=lambda alpha, Re, mach, deflection:
( # Profile drag coefficient function
(1 + (alpha / 5)**2) * 2 * Cf_flat_plate(Re_L=Re)),
CM_function=lambda alpha, Re, mach, deflection:
( # Moment coefficient function about quarter-chord