SUAVE.Components.Energy.Converters.Supersonic_Nozzle.Supersonic_Nozzle Class Reference

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

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

Public Attributes
	tag
	polytropic_efficiency
	pressure_ratio
	pressure_recovery
	max_area_ratio
	min_area_ratio
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.
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.Supersonic_Nozzle.Supersonic_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.Supersonic_Nozzle.Supersonic_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

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

Inputs:
conditions.freestream.
  isentropic_expansion_factor         [-]
  specific_heat_at_constant_pressure  [J/(kg K)]
  pressure                            [Pa]
  stagnation_pressure                 [Pa]
  stagnation_temperature              [K]
  gas_specific_constant               [J/(kg K)]
  mach_number                         [-]
self.inputs.
  stagnation_temperature              [K]
  stagnation_pressure                 [Pa]
   
Outputs:
self.outputs.
  stagnation_temperature              [K]  
  stagnation_pressure                 [Pa]
  stagnation_enthalpy                 [J/kg]
  mach_number                         [-]
  static_temperature                  [K]
  static_enthalpy                     [J/kg]
  velocity                            [m/s]
  static_pressure                     [Pa]
  area_ratio                          [-]

Properties Used:
self.
  pressure_ratio                      [-]
  polytropic_efficiency               [-]
  pressure_recovery                   [-]

compute_limited_geometry()

def SUAVE.Components.Energy.Converters.Supersonic_Nozzle.Supersonic_Nozzle.compute_limited_geometry	(		self,
			conditions
	)

This is a variable geometry nozzle component that allows 
for supersonic outflow. all possible nozzle conditions, including 
overexpansion and underexpansion.

Assumptions:
Constant polytropic efficiency and pressure ratio

Source:
https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/
https://web.stanford.edu/~cantwell/AA210A_Course_Material/AA210A_Course_Notes/

Inputs:
conditions.freestream.
  isentropic_expansion_factor         [-]
  specific_heat_at_constant_pressure  [J/(kg K)]
  pressure                            [Pa]
  stagnation_pressure                 [Pa]
  stagnation_temperature              [K]
  gas_specific_constant               [J/(kg K)] 
  mach_number                         [-]
self.inputs.
  stagnation_temperature              [K]
  stagnation_pressure                 [Pa]
   
Outputs:
self.outputs.
  stagnation_temperature              [K]  
  stagnation_pressure                 [Pa]
  stagnation_enthalpy                 [J/kg]
  mach_number                         [-]
  static_temperature                  [K]
  static_enthalpy                     [J/kg]
  velocity                            [m/s]
  static_pressure                     [Pa]

Properties Used:
self.
  pressure_ratio                      [-]
  polytropic_efficiency               [-]
  max_area_ratio                      [-]
  min_area_ratio                      [-]

compute_scramjet()

def SUAVE.Components.Energy.Converters.Supersonic_Nozzle.Supersonic_Nozzle.compute_scramjet	(		self,
			conditions
	)

This computes exit conditions of a scramjet. 

Assumptions: 
Fixed output Cp and Gamma 

Source: 
Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M.,  
"Hypersonic Airbreathing Propulsion", 1994  
Chapter 4 - pgs. 175-180

Inputs:  
conditions.freestream.  
   isentropic_expansion_factor         [-]  
   specific_heat_at_constant_pressure  [J/(kg K)]  
   pressure                            [Pa]  
   stagnation_pressure                 [Pa]  
   stagnation_temperature              [K]  
   gas_specific_constant               [J/(kg K)]  
   mach_number                         [-]  

self.inputs.  
   stagnation_temperature              [K]  
   stagnation_pressure                 [Pa]  

Outputs:  
self.outputs.  
   stagnation_temperature              [K]    
   stagnation_pressure                 [Pa]  
   stagnation_enthalpy                 [J/kg]  
   mach_number                         [-]  
   static_temperature                  [K]  
   static_enthalpy                     [J/kg]  
   velocity                            [m/s]  
   static_pressure                     [Pa]  
   area_ratio                          [-]  

Properties Used:  
self.  
   polytropic_efficiency               [-]  
   pressure_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/Supersonic_Nozzle.py