fastga.models.aerodynamics.components.compute_cn_aileron module

Estimation of rolling moment du to the ailerons.

class fastga.models.aerodynamics.components.compute_cn_aileron.ComputeCnDeltaAileron(**kwargs)

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

Yaw moment due to aileron deflection (also called adverse aileron yaw). Depends on the wing lift, hence on the 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.

Based on [Ros85b] section 10.3.8.

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.