SUAVE.Components.Energy.Networks.Scramjet.Scramjet Class Reference

Inheritance diagram for SUAVE.Components.Energy.Networks.Scramjet.Scramjet:

Public Member Functions
def	__defaults__ (self)
def	evaluate_thrust (self, state)

Public Attributes
	tag
	number_of_engines
	engine_length
	generative_design_minimum
Public Attributes inherited from SUAVE.Components.Energy.Networks.Network.Network
	tag
	generative_design_max_per_vehicle
	non_dimensional_origin
	number_of_engines
	engine_length
	wing_mounted
	areas
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 scramjet for hypersonic flight. 

    Assumptions: 
    Currently implements Stream Function Method
    Combustion, Thermochemical Properties are estimated (HAP in below reference unavailable)
    Assumes no spillage drag at the momement
    Shock-BL Interaction negected
    
    Source: 
    Most of the componentes come from this book: 
    Heiser, William H., Pratt, D. T., Daley, D. H., and Unmeel, B. M., 
    "Hypersonic Airbreathing Propulsion", 1994 
    Chapter 4 - pgs. 175-180

Member Function Documentation

__defaults__()

def SUAVE.Components.Energy.Networks.Scramjet.Scramjet.__defaults__

(

self

)

This sets the default values for the network to function. 

    Assumptions: 
    None 

    Source: 
    N/A 

    Inputs: 
    None 

    Outputs: 
    None 

    Properties Used: 
    N/A 

Reimplemented from SUAVE.Components.Energy.Networks.Network.Network.

evaluate_thrust()

def SUAVE.Components.Energy.Networks.Scramjet.Scramjet.evaluate_thrust	(		self,
			state
	)

Calculate thrust given the current state of the vehicle 

Assumptions: 
None 

Source: 
N/A 

Inputs: 
state [state()] 

Outputs: 
results.thrust_force_vector                   [N] 
results.vehicle_mass_rate                     [kg/s] 

conditions.noise.sources.scramjets:
core: 
exit_static_temperature                  [K]  
exit_static_pressure                     [K]  
exit_stagnation_temperature              [K]  
exit_stagnation_pressure                 [Pa]  
exit_velocity                            [m/s]  
fan: 
exit_static_temperature                  [K]   
exit_static_pressure                     [K]  
exit_stagnation_temperature              [K]  
exit_stagnation_pressure                 [Pa]  
exit_velocity                            [m/s]  

Properties Used: 
Defaulted values 

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

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Components/Energy/Networks/Scramjet.py