fastga.models.aerodynamics.components.compute_cy_rudder module

Estimation of yawing moment du to the rudder.

class fastga.models.aerodynamics.components.compute_cy_rudder.ComputeCyDeltaRudder(**kwargs)[source]

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

Yawing moment due to rudder estimated based on the methodology in section 10.3.8 of Roskam without the surface ratio to keep the coefficient relative to the VT area and dividing by the theoretical airfoil lift coefficient as suggested by the formulae giving the wing lift increment due to flap deployment which can be considered similar

Based on : Roskam, Jan. Airplane Design: Part 6-Preliminary Calculation of Aerodynamic, Thrust and Power Characteristics. DARcorporation, 1985.

Store some bound methods so we can detect runtime overrides.

initialize()[source]

Declaring the low_speed_aero options so we can use low speed and cruise conditions.

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.