Source code for RCAIDE.Library.Components.Powertrain.Converters.Supersonic_Nozzle
# RCAIDE/Library/Components/Propulsors/Converters/Compressor.py
# (c) Copyright 2023 Aerospace Research Community LLC
#
# Created: Feb 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from .Converter import Converter
from RCAIDE.Library.Methods.Powertrain.Converters.Supersonic_Nozzle.append_supersonic_nozzle_conditions import append_supersonic_nozzle_conditions
# ----------------------------------------------------------------------------------------------------------------------
# Compressor
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Supersonic_Nozzle(Converter):
"""
A supersonic nozzle component model for propulsion systems capable of supersonic outflow.
Attributes
----------
tag : str
Identifier for the nozzle. Default is 'Supersonic_Nozzle'.
polytropic_efficiency : float
Efficiency of the expansion process accounting for losses. Default is 1.0.
pressure_ratio : float
Ratio of outlet to inlet pressure. Default is 1.0.
pressure_recovery : float
Ratio of recovered to ideal total pressure. Default is 1.0.
max_area_ratio : float
Maximum allowable exit to throat area ratio. Default is 1000.0.
min_area_ratio : float
Minimum allowable exit to throat area ratio. Default is 0.0.
Notes
-----
The Supersonic_Nozzle class models a convergent-divergent nozzle that can
achieve supersonic exit flow. The model includes:
* Isentropic flow relations
* Shock wave effects
* Variable area ratio capabilities
* Real gas effects through efficiency terms
* Pressure recovery modeling
**Major Assumptions**
* Pressure ratio and efficiency do not change with varying conditions
* One-dimensional flow
* Perfect gas behavior
* Adiabatic process
* No boundary layer separation
* Steady flow conditions
**Definitions**
'Polytropic Efficiency'
Measure of expansion process efficiency accounting for losses
'Pressure Ratio'
Ratio of exit static pressure to inlet total pressure
'Pressure Recovery'
Measure of total pressure preservation through the nozzle
'Area Ratio'
Ratio of exit area to throat area
References
----------
[1] Mattingly, J. D., & Boyer, K. M. (2016). Elements of propulsion: Gas
turbines and rockets, second edition Jack D. Mattingly, Keith M. Boyer.
American Institute of Aeronautics and Astronautics.
See Also
--------
RCAIDE.Library.Components.Component
RCAIDE.Library.Components.Powertrain.Converters.Expansion_Nozzle
"""
def __defaults__(self):
""" This sets the default values for the component to function.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
None
"""
#set the defaults
self.tag = 'Supersonic_Nozzle'
self.polytropic_efficiency = 1.0
self.pressure_ratio = 1.0
self.pressure_recovery = 1.0
self.max_area_ratio = 1000.
self.min_area_ratio = 0.
[docs]
def append_operating_conditions(self,segment,energy_conditions,noise_conditions=None):
append_supersonic_nozzle_conditions(self,segment,energy_conditions)
return
