SUAVE.Components.Energy.Converters.Compression_Nozzle.Compression_Nozzle Class Reference

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

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

Public Attributes
	tag
	polytropic_efficiency
	pressure_ratio
	pressure_recovery
	compressibility_effects
	compression_levels
	theta
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 intended for use in compression.
Calling this class calls the compute function.

Assumptions:
Pressure ratio and efficiency do not change with varying conditions.
Subsonic or choked output.

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

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Converters.Compression_Nozzle.Compression_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.Compression_Nozzle.Compression_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
Adiabatic

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]
  gas_specific_constant               [J/(kg K)]
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]

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

compute_scramjet()

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

This function computes the compression of a scramjet 
using shock trains.  
    
Assumptions: 
    
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] 
   gas_specific_constant              [J/(kg K)] 
   temperature                        [K] 
   mach_number                        [-] 
   velocity                           [m/s] 
    
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] 
   specific_heat_at_constant_pressure [J/(kg K)] 
    
Properties Used: 
self. 
   efficiency                         [-] 
   shock_count                        [-] 
   theta                              [Rad] 

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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/Compression_Nozzle.py