fastga.models.aerodynamics.components.wing.compute_cm_pitch_rate_wing module

class fastga.models.aerodynamics.components.wing.compute_cm_pitch_rate_wing.ComputeCMPitchVelocityWing(**kwargs)[source]

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

Class to compute the contribution of the wing to the pitch moment coefficient due to pitch rate. The vertical distance between the cg and the aerodynamic center of teh plane is taken equal to the vertical distance between the root chord and the fuselage centerline. The convention from [Ros85b] are used, meaning that, for the derivative with respect to a pitch rate, this rate is made dimensionless by multiplying it by the MAC and dividing it by 2 times the airspeed.

Based on [Gud13].

Store some bound methods so we can detect runtime overrides.

initialize()[source]

Perform any one-time initialization run at instantiation.

setup()[source]

Declare inputs and outputs.

Available attributes:

name pathname comm options

compute(inputs, outputs, discrete_inputs=None, discrete_outputs=None)[source]

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.