SUAVE.Components.Energy.Converters.de_Laval_Nozzle.de_Laval_Nozzle Class Reference

Inheritance diagram for SUAVE.Components.Energy.Converters.de_Laval_Nozzle.de_Laval_Nozzle:

Public Member Functions
def	__defaults__ (self)
def	compute (self, conditions)

Public Attributes
	tag
	polytropic_efficiency
	pressure_ratio_converge
	pressure_ratio_diverge
	expansion_ratio
	area_throat
Public Attributes inherited from SUAVE.Components.Energy.Energy_Component.Energy_Component
	inputs
	outputs
Public Attributes inherited from SUAVE.Components.Physical_Component.Physical_Component
	tag
	mass_properties
	origin
	symmetric
Public Attributes inherited from SUAVE.Components.Component.Component
	tag
	origin
	generative_design_max_per_vehicle
	generative_design_characteristics
	generative_design_special_parent

Detailed Description

This is a nozzle component that allows for supersonic outflow. 
This is a converging-diverging nozzle used primarilty in rockets.
Calling this class calls the compute function.

Assumptions:
Pressure ratio and efficiency do not change with varying conditions.

Source:

https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Converters.de_Laval_Nozzle.de_Laval_Nozzle.__defaults__

(

self

)

This sets the default values for the component to function.

Assumptions:
None
    
Source:
N/A
    
Inputs:
None
    
Outputs:
None
    
Properties Used:
None

Reimplemented from SUAVE.Components.Energy.Energy_Component.Energy_Component.

compute()

def SUAVE.Components.Energy.Converters.de_Laval_Nozzle.de_Laval_Nozzle.compute	(		self,
			conditions
	)

This computes the output values from the input values according to
equations from the source.

Assumptions:
Constant polytropic efficiency and pressure ratio
Isentropic Process from chamber to throat (Pt_throat = Pt2)
Supersonic/Throat is Choked

Source:
Chapter 7
https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/

Inputs:
self.inputs.
  combustion_temperature              [k]
  combustion_pressure                 [Pa]
  isentropic_expansion_factor         [-]
  gas_specific_constant               [J/(kg-K)]
             
Outputs:
self.outputs.
  stagnation_pressure                 [Pa]
  stagnation_temperature              [K]  
  static_temperature                  [K]
  static_pressure                     [Pa]
  mach_number                         [-]
  velocity                            [m/s]

Properties Used:
self.
  pressure_ratio                      [-]
  polytropic_efficiency               [-]
  area_throat                         [m^2]
  expansion_ratio                     [-]

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The documentation for this class was generated from the following file:

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Components/Energy/Converters/de_Laval_Nozzle.py