aircraft.models.aerodynamics.simple_lift_model

Module Contents

Classes

SimpleLiftModel	Implements semi-empirical formula for 3D lift curve slope.
SimpleLiftModelInputs

Attributes

theta

class aircraft.models.aerodynamics.simple_lift_model.SimpleLiftModel

Implements semi-empirical formula for 3D lift curve slope.

We then compute the lift based on the angle of attack.

evaluate(inputs: SimpleLiftModelInputs)

class aircraft.models.aerodynamics.simple_lift_model.SimpleLiftModelInputs

AR: Union[float, int, csdl_alpha.Variable]

Cl_0: Union[float, int, csdl_alpha.Variable]

Cl_alpha: Union[float, int, csdl_alpha.Variable]

S_ref: Union[float, int, csdl_alpha.Variable]

S_wet: Union[float, int, csdl_alpha.Variable]

ac_states: CADDEE_alpha.core.aircraft.conditions.aircraft_condition.AircaftStates

atmos_state: CADDEE_alpha.core.aircraft.models.atmosphere.simple_atmosphere_model.AtmosphericStates

d_fuse: Union[float, int, csdl_alpha.Variable]

max_sweep: Union[float, int, csdl_alpha.Variable]

quarter_chord: Union[float, int, csdl_alpha.Variable, None]

wing_incidence: Union[float, int, csdl_alpha.Variable, None]

aircraft.models.aerodynamics.simple_lift_model.theta