Source code for RCAIDE.Library.Attributes.Propellants.JP7
# RCAIDE/Library/Attributes/Propellants/JP7.py
#
#
# Created: Mar 2024, M. Clarke
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# Imports
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from .Propellant import Propellant
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# JP7 Propellant Class
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[docs]
class JP7(Propellant):
"""
A class representing JP-7 high thermal stability jet fuel properties. This specialized
fuel was developed for high-speed aircraft operating at elevated temperatures.
Attributes
----------
tag : str
Identifier for the propellant ('JP7')
reactant : str
Oxidizer used for combustion ('O2')
density : float
Fuel density in kg/m³ (803.0)
specific_energy : float
Specific energy content in J/kg (43.50e6)
energy_density : float
Energy density in J/m³ (34930.5e6)
stoichiometric_fuel_to_air : float
Stoichiometric fuel-to-air ratio (0.0674)
temperatures : Data
Critical temperatures in K
- flash : float
Flash point (333.15)
- autoignition : float
Autoignition temperature (555.15)
- freeze : float
Freezing point (514.15)
Notes
-----
JP-7 is a specialized jet fuel developed for the SR-71 Blackbird and similar
high-speed aircraft. It features high thermal stability and low volatility for
operation at elevated temperatures.
**Definitions**
'Flash Point'
Lowest temperature at which fuel vapors will ignite (60°C, significantly
higher than conventional jet fuels)
'Thermal Stability'
Resistance to thermal decomposition at elevated temperatures
'Stoichiometric Fuel-to-Air Ratio'
Ideal fuel-to-air mass ratio for complete combustion
**Major Assumptions**
* Properties are for standard temperature and pressure conditions (15C, 1atm)
References
----------
[1] Roberts, K. (2008). ANALYSIS AND DESIGN OF A HYPERSONIC SCRAMJET ENGINE WITH A STARTING MACH NUMBER OF 4.00 (thesis). UTA. University of Texas at Austin. Retrieved December 30, 2024, from https://arc.uta.edu/publications/td_files/Kristen%20Roberts%20MS.pdf.
"""
def __defaults__(self):
"""This sets the default values.
Assumptions:
None
Source:
http://arc.uta.edu/publications/td_files/Kristen%20Roberts%20MS.pdf
"""
self.tag = 'JP7'
self.reactant = 'O2'
self.density = 803.0 # kg/m^3 (15 C, 1 atm)
self.specific_energy = 43.50e6 # J/kg
self.energy_density = 34930.5e6 # J/m^3
self.stoichiometric_fuel_to_air = 0.0674
# critical temperatures
self.temperatures.flash = 333.15 # K
self.temperatures.autoignition = 555.15 # K
self.temperatures.freeze = 514.15 # K
self.stoichiometric_fuel_air_ratio = 0 # [-] Stoichiometric Fuel to Air ratio
self.heat_of_vaporization = 0 # [J/kg] Heat of vaporization at standard conditions
self.temperature = 0 # [K] Temperature of fuel
self.pressure = 0 # [Pa] Pressure of fuel
self.fuel_surrogate_S1 = {} # [-] Mole fractions of fuel surrogate species
self.kinetic_mechanism = '' # [-] Kinetic mechanism for fuel surrogate species
self.oxidizer = ''
