SUAVE  2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft

Functions to perform low-fidelity lift calculations. More...

Functions

def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_flap_lift.compute_flap_lift (t_c, flap_type, flap_chord, flap_angle, sweep, wing_Sref, wing_affected_area)
 
def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_max_lift_coeff.compute_max_lift_coeff (state, settings, geometry)
 
def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_slat_lift.compute_slat_lift (slat_angle, sweep_angle)
 

Detailed Description

Functions to perform low-fidelity lift calculations.

Function Documentation

◆ compute_flap_lift()

def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_flap_lift.compute_flap_lift (   t_c,
  flap_type,
  flap_chord,
  flap_angle,
  sweep,
  wing_Sref,
  wing_affected_area 
)
Computes the increase of lift due to trailing edge flap deployment

Assumptions:
None

Source:
Unknown

Inputs:
t_c                 (wing thickness ratio)                 [Unitless]
flap_type                                                  [string]
flap_c_chord        (flap chord as fraction of wing chord) [Unitless]
flap_angle          (flap deflection)                      [radians]
sweep               (Wing sweep angle)                     [radians]
wing_Sref           (Wing reference area)                  [m^2]
wing_affected_area  (Wing area affected by flaps)          [m^2]

Outputs:
dcl_max_flaps       (Lift coefficient increase)            [Unitless]

Properties Used:
N/A

◆ compute_max_lift_coeff()

def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_max_lift_coeff.compute_max_lift_coeff (   state,
  settings,
  geometry 
)
Computes the maximum lift coefficient associated with an aircraft high lift system

Assumptions:
None

Source:
Unknown

Inputs:
analyses.max_lift_coefficient_factor       [Unitless]
vehicle.reference_area                     [m^2]
vehicle.wings.                             
  areas.reference                          [m^2]
  thickness_to_chord                       [Unitless]
  chords.mean_aerodynamic                  [m]
  sweeps.quarter_chord                     [radians]
  taper                                    [Unitless]
  flaps.chord                              [m]
 control_surfaces.flap.deflection          [radians]
 control_surfaces.slat.deflection          [radians]
  areas.affected                           [m^2]
  control_surfaces.flap.configuration_type [string]
conditions.freestream.                     
  velocity                                 [m/s]
  density                                  [kg/m^3]
  dynamic_viscosity                        [N s/m^2]
                                           
Outputs:                                   
Cl_max_ls (maximum CL)                     [Unitless]
Cd_ind    (induced drag)                   [Unitless]

Properties Used:
N/A

◆ compute_slat_lift()

def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_slat_lift.compute_slat_lift (   slat_angle,
  sweep_angle 
)
Computes the increase in lift due to slats

Assumptions:
None

Source:
adg.stanford.edu (Stanford AA241 A/B Course Notes)

Inputs:
slat_angle   [radians]
sweep_angle  [radians]

Outputs:
dcl_slat     [Unitless]

Properties Used:
N/A