fastga.models.aerodynamics.components.wing.compute_cn_roll_rate_wing module
- class fastga.models.aerodynamics.components.wing.compute_cn_roll_rate_wing.ComputeCnRollRateWing(**kwargs)[source]
Bases:
fastga.models.aerodynamics.components.figure_digitization.FigureDigitizationClass to compute the contribution of the wing to the yaw moment coefficient due to roll 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. Flap deflection effect is neglected. 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 10.2.6. The reference point for the CG was taken to be equal to the wing quarter chord to match what is taken for other coefficient. The change in reference point is not easy for this coefficient as it only affect part of the coefficient (the wing lift contribution), this coefficient might thus need to be recomputed “on the fly” for future stability computation. This is has no influence for unswept wing as in any case it was multiplied by tan(sweep_25).
Store some bound methods so we can detect runtime overrides.
- 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.