AERODAS

Functions to perform calculations according to AERODAS models. More...

Functions
def	SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.setup_data (state, settings, geometry)
def	SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.lift_drag_total (state, settings, geometry)
def	SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.drag_total (state, settings, geometry)
def	SUAVE.Methods.Aerodynamics.AERODAS.finite_aspect_ratio.finite_aspect_ratio (state, settings, geometry)
def	SUAVE.Methods.Aerodynamics.AERODAS.post_stall_coefficients.post_stall_coefficients (state, settings, geometry)
def	SUAVE.Methods.Aerodynamics.AERODAS.pre_stall_coefficients.pre_stall_coefficients (state, settings, geometry)

Detailed Description

Functions to perform calculations according to AERODAS models.

Function Documentation

drag_total()

def SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.drag_total	(		state,
			settings,
			geometry
	)

Extract the drag coefficient

Assumptions:
None

Source:
N/A

Inputs:
state.conditions.aerodynamics.drag_coefficient [Unitless]

Outputs:
CD (coefficient of drag)                       [Unitless]

Properties Used:
N/A

finite_aspect_ratio()

def SUAVE.Methods.Aerodynamics.AERODAS.finite_aspect_ratio.finite_aspect_ratio	(		state,
			settings,
			geometry
	)

Uses the AERODAS method to prestall parameters for lift and drag.

Assumptions:
None

Source:
NASA TR: "Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in
  Wind Turbines and Wind Tunnels" by D. A. Spera

Inputs:
geometry.
  aspect_ratio                                [Unitless]
  section.
    maximum_coefficient_lift                  [Unitless]
    angle_attack_max_prestall_lift            [radians]
    pre_stall_maximum_drag_coefficient_angle  [radians]
    pre_stall_maximum_drag_coefficient        [Unitless]
settings.section_lift_curve_slope             [radians]

Outputs:
pre_stall_maximum_lift_coefficient            [Unitless]
pre_stall_maximum_lift_drag_coefficient       [Unitless]
pre_stall_lift_curve_slope                    [radians]
pre_stall_maximum_drag_coefficient_angle      [Unitless]
(these are also packed into geometry.)

Properties Used:
N/A

lift_drag_total()

def SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.lift_drag_total	(		state,
			settings,
			geometry
	)

This sums lift and drag contributions from all of the wings.

Assumptions:
None

Source:
NASA TR: "Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in
  Wind Turbines and Wind Tunnels" by D. A. Spera

Inputs:
geometry.
  reference_area                                                      [m^2]
  wings
state.conditions.aerodynamics.
  angle_of_attack                                                     [radians]
  pre_stall_coefficients[wing.tag].lift_coefficient (for each wing)   [Unitless]
  pre_stall_coefficients[wing.tag].drag_coefficient (for each wing)   [Unitless]
  post_stall_coefficients[wing.tag].lift_coefficient (for each wing)  [Unitless]
  post_stall_coefficients[wing.tag].drag_coefficient (for each wing)  [Unitless]
settings.section_zero_lift_angle_of_attack                            [radians]

Outputs:
state.conditions.aerodynamics.
  lift_coefficient                                                    [Unitless]
  drag_coefficient                                                    [Unitless]

Properties Used:
N/A

post_stall_coefficients()

def SUAVE.Methods.Aerodynamics.AERODAS.post_stall_coefficients.post_stall_coefficients	(		state,
			settings,
			geometry
	)

Uses the AERODAS method to determine poststall parameters for lift and drag for a single wing

Assumptions:
None

Source:
NASA TR: "Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in
  Wind Turbines and Wind Tunnels" by D. A. Spera

Inputs:
settings.section_zero_lift_angle_of_attack      [radians]
geometry.
  aspect_ratio                                  [Unitless]
  thickness_to_chord                            [Unitless]
  section.angle_attack_max_prestall_lift        [radians]
  pre_stall_maximum_lift_drag_coefficient       [Unitless]
  pre_stall_maximum_drag_coefficient_angle      [Unitless]
state.conditions.aerodynamics.angle_of_attack   [radians]
  

Outputs:
CL2 (coefficient of lift)                       [Unitless]
CD2 (coefficient of drag)                       [Unitless]
(packed in state.conditions.aerodynamics.post_stall_coefficients[geometry.tag])

Properties Used:
N/A

pre_stall_coefficients()

def SUAVE.Methods.Aerodynamics.AERODAS.pre_stall_coefficients.pre_stall_coefficients	(		state,
			settings,
			geometry
	)

Uses the AERODAS method to determine prestall parameters for lift and drag for a single wing

Assumptions:
None

Source:
NASA TR: "Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in
  Wind Turbines and Wind Tunnels" by D. A. Spera

Inputs:
state.conditions.aerodynamics.angle_of_attack
settings.section_zero_lift_angle_of_attack
geometry.
  section.
    angle_attack_max_prestall_lift
    zero_lift_drag_coefficient
  pre_stall_maximum_drag_coefficient_angle
  pre_stall_maximum_lift_coefficient
  pre_stall_lift_curve_slope 
  pre_stall_maximum_lift_drag_coefficient

Outputs:
CL1 (coefficient of lift)                       [Unitless]
CD1 (coefficient of drag)                       [Unitless]
(packed in state.conditions.aerodynamics.pre_stall_coefficients[geometry.tag])

Properties Used:
N/A

setup_data()

def SUAVE.Methods.Aerodynamics.AERODAS.AERODAS_setup.setup_data	(		state,
			settings,
			geometry
	)

This sets up the data structure for pre and post stall coefficients
that will be generated by the AERODAS model.

Assumptions:
None

Source:
NASA TR: "Models of Lift and Drag Coefficients of Stalled and Unstalled Airfoils in
  Wind Turbines and Wind Tunnels" by D. A. Spera

Inputs:
state.conditions.aerodynamics (to be modified)

Outputs:
None

Properties Used:
N/A