Results

Miscellaneous functions to print results. More...

Functions
def	SUAVE.Input_Output.Results.print_compress_drag.print_compress_drag (vehicle, analyses, filename='compress_drag.dat')
def	SUAVE.Input_Output.Results.print_engine_data.print_engine_data (vehicle, filename='engine_data.dat', units="imperial")
def	SUAVE.Input_Output.Results.print_mission_breakdown.print_mission_breakdown (results, filename='mission_breakdown.dat', units="imperial")
def	SUAVE.Input_Output.Results.print_parasite_drag.print_parasite_drag (ref_condition, vehicle, analyses, filename='parasite_drag.dat')
def	SUAVE.Input_Output.Results.print_weights.print_weight_breakdown (config, filename='weight_breakdown.dat')
	print_weights.py More...

Detailed Description

Miscellaneous functions to print results.

Function Documentation

print_compress_drag()

def SUAVE.Input_Output.Results.print_compress_drag.print_compress_drag	(		vehicle,
			analyses,
			filename = 'compress_drag.dat'
	)

This creates a file showing a breakdown of compressibility drag for the vehicle.

Assumptions:
None

Source:
N/A

Inputs:
vehicle.wings.main_wing.
  sweeps.quarter_chord     [-]
vehicle.wings.*.
  tag                     <string>
  thickness_to_chord      [-]
vehicle.
  tag                     <string>
  reference_area          [m^2]
analyses.configs.cruise.aerodynamics.settings    Used in called function:
analyses.configs.cruise.aerodynamics.process.compute.drag.compressibility.wings.wing(state,settings,wing)
filename                  Sets file name to save (optional)


Outputs:
filename                  Saved file with name as above

Properties Used:
N/A

print_engine_data()

def SUAVE.Input_Output.Results.print_engine_data.print_engine_data	(		vehicle,
			filename = 'engine_data.dat',
			units = "imperial"
	)

This creates a file showing engine information.

Assumptions:
One network (can be multiple engines) with 'turbofan' tag.

Source:
N/A

Inputs:
vehicle.
  tag
  turbofan()              Function to compute thrust and fuel burn rate
  networks.turbofan.
    design_thrust         [N]
    engine_length         [m]
    thrust.bypass_ratio   [-] 
filename (optional)       <string> Determines the name of the saved file
units (optional)          <string> Determines the type of units used in the output, options are imperial and si

Outputs:
filename                  Saved file with name as above

Properties Used:
N/A

print_mission_breakdown()

def SUAVE.Input_Output.Results.print_mission_breakdown.print_mission_breakdown	(		results,
			filename = 'mission_breakdown.dat',
			units = "imperial"
	)

This creates a file showing mission information.

Assumptions:
None

Source:
N/A

Inputs:
results.segments.*.conditions.
  frames.
    inertial.position_vector     [m]
    inertial.time                [s]
  aerodynamics.lift_coefficient  [-]
  weights.total                  [kg]
  weights.fuel_mass              [kg]
  weights.additional_fuel_mass   [kg]
  freestream.  
    mach_number                  [-]
    pressure                     [Pa]
filename (optional)       <string> Determines the name of the saved file
units (option)            <string> Determines the type of units used in the output, options are imperial and si

Outputs:
filename                  Saved file with name as above

Properties Used:
N/A

print_parasite_drag()

def SUAVE.Input_Output.Results.print_parasite_drag.print_parasite_drag	(		ref_condition,
			vehicle,
			analyses,
			filename = 'parasite_drag.dat'
	)

This creates a file showing a breakdown of compressibility drag for the vehicle. Esimates
altitude based on reference conditions.

Assumptions:
None

Source:
N/A

Inputs:
ref_condition.
  mach_number
  reynolds_number
vehicle.wings.main_wing.
  chords.mean_aerodynamic
  aspect_ratio
  sweeps.quarter_chord     [-]
  thickness_to_chord
  taper
vehicle.wings.*.
  tag                     <string>
vehicle.reference_area    [m^2]
analyses.configs.cruise.aerodynamics.settings    Used in called functions:
  compute.parasite.wings.wing(state,settings,wing)                (for all wings)
  compute.parasite.fuselages.fuselage(state,settings,fuselage)    (for all fuselages)
  compute.parasite.nacelles.nacelle(state,settings,nacelle) (for all nacelles)
  compute.parasite.pylons(state,settings,vehicle) 
  compute.miscellaneous(state,settings,vehicle)
  compute.parasite.total(state,settings,vehicle)
  compute.induced(state,settings,vehicle)    
    with compute = analyses.configs.cruise.aerodynamics.process.compute.drag
filename                  Sets file name to save (optional)


Outputs:
filename                  Saved file with name as above

Properties Used:
N/A

print_weight_breakdown()

def SUAVE.Input_Output.Results.print_weights.print_weight_breakdown	(		config,
			filename = 'weight_breakdown.dat'
	)

print_weights.py

This creates a file showing weight information.

Assumptions:
One network (can be multiple engines) with 'turbofan' tag.

Source:
N/A

Inputs:
config.
  weight_breakdown.
    empty
    *.tag            <string>
    systems.*.tag    <string>
  mass_properties.
    max_takeoff      [kg]
max_landing      [kg]
max_zero_fuel    [kg]
max_fuel         [kg]
max_payload      [kg]
filename (optional)  <string> Determines the name of the saved file

Outputs:
filename              Saved file with name as above

Properties Used:
N/A