fastoad.models.aerodynamics.components.utils.cd0_lifting_surface module

Computation of CD0 for a lifting surface.

class fastoad.models.aerodynamics.components.utils.cd0_lifting_surface.LiftingSurfaceGeometry(thickness_ratio: float, MAC_length: float, sweep_angle_25: float, cambered: bool, wet_area: float, interaction_coeff: float)[source]

Bases: object

Minimum geometry data for computation of CD0 of lifting surfaces.

thickness_ratio: float

average thickness ratio

MAC_length: float

length of Mean Aerodynamic Chord

sweep_angle_25: float

sweep angle at 25% chord, in degrees

cambered: bool

True if airfoil is cambered

wet_area: float

wet surface area of the lifting surface

interaction_coeff: float

ratio of additional drag due to interaction effects

fastoad.models.aerodynamics.components.utils.cd0_lifting_surface.compute_cd0_lifting_surface(geometry: fastoad.models.aerodynamics.components.utils.cd0_lifting_surface.LiftingSurfaceGeometry, mach: float, reynolds: float, wing_area: float, lift_coefficient: float = 0.0)[source]

Computes CD0 for a lifting surface.

Friction coefficient is assessed from [Ray99] (Eq 12.27). Corrections for lifting surfaces are from [DCAC14].

Parameters

  • geometry – definition of lifting surface geometry

  • mach – Mach number

  • reynolds – Reynolds number

  • wing_area – wing area (will be used for getting CD specific to wing area

  • lift_coefficient – needed if wing is cambered

Returns

CD0 value