clcd

class clcd.CLCD(**kwargs)

Bases: openmdao.components.meta_model_structured_comp.MetaModelStructuredComp

Computes aerodynamic lift and drag coefficients from aerodynamics data tables.

The CLCD component requires the following inputs:

• inputs['alpha']: aircraft angle of attack [deg]

• inputs['theta_flaps']: aircraft flap deflection angle [deg]

• inputs['theta_slats']: aircraft slat deflection angle [deg]

The CLCD component computes the following outputs:

• outputs['c_l']: aircraft lift coefficient [-]

• outputs['c_l_max']: maximum aircraft lift coefficient [-]

• outputs['c_d']: aircraft drag coefficient [-]

initialize()

Initialize the component.

setup()

Declare inputs and outputs.

Available attributes:

name pathname comm options