Functions to perform low-fidelity lift calculations.
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Functions to perform low-fidelity lift calculations.
◆ compute_flap_lift()
def SUAVE.Methods.Aerodynamics.Fidelity_Zero.Lift.compute_flap_lift.compute_flap_lift |
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t_c, |
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flap_type, |
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flap_chord, |
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flap_angle, |
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sweep, |
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wing_Sref, |
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wing_affected_area |
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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 |
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state, |
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settings, |
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geometry |
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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 |
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slat_angle, |
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sweep_angle |
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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