fastga.models.aerodynamics.components.wing.compute_cl_yaw_rate_wing module

class fastga.models.aerodynamics.components.wing.compute_cl_yaw_rate_wing.ComputeClYawRateWing(**kwargs)

Bases: fastga.models.aerodynamics.components.figure_digitization.FigureDigitization

Class to compute the contribution of the wing to the roll moment coefficient due to yaw rate. Depends on the lift coefficient of the wing, hence on the reference angle of attack, so the same remark as in ..compute_cy_yaw_rate.py holds. The convention from [Ros85b] are used, meaning that for lateral derivative, the reference length is the wing span. Another important point is that, for the derivative with respect to yaw and roll, the rotation speed are made dimensionless by multiplying them by the wing span and dividing them by 2 times the airspeed.

Based on [Ros85b] section 10.2.8

Store some bound methods so we can detect runtime overrides.

initialize()

Perform any one-time initialization run at instantiation.

setup()

Declare inputs and outputs.

Available attributes:

name pathname comm options

compute(inputs, outputs, discrete_inputs=None, discrete_outputs=None)

Compute outputs given inputs. The model is assumed to be in an unscaled state.

Parameters

• inputs (Vector) – Unscaled, dimensional input variables read via inputs[key].

• outputs (Vector) – Unscaled, dimensional output variables read via outputs[key].

• discrete_inputs (dict or None) – If not None, dict containing discrete input values.

• discrete_outputs (dict or None) – If not None, dict containing discrete output values.