# Path: proptools/isentropic.py
# def stag_temperature_ratio(M, gamma):
# def stag_pressure_ratio(M, gamma):
# def stag_density_ratio(M, gamma):
# def velocity(v_1, p_1, T_1, p_2, gamma, m_molar):    # pylint: disable=too-many-arguments


from proptools import isentropic
"""Estimate exit velocity."""

# Declare engine design parameters
p_c = 10e6    # Chamber pressure [units: pascal]
p_e = 100e3    # Exit pressure [units: pascal]
gamma = 1.2    # Exhaust heat capacity ratio [units: dimensionless]
m_molar = 20e-3    # Exhaust molar mass [units: kilogram mole**1]
T_c = 3000.    # Chamber temperature [units: kelvin]

# Compute the exit velocity

# Path: proptools/isentropic.py
# def stag_temperature_ratio(M, gamma):
# def stag_pressure_ratio(M, gamma):
# def stag_density_ratio(M, gamma):
# def velocity(v_1, p_1, T_1, p_2, gamma, m_molar):    # pylint: disable=too-many-arguments


# Path: docs/source/examples/exit_velocity.py
from proptools import isentropic

"""Estimate exit velocity."""

# Declare engine design parameters
p_c = 10e6    # Chamber pressure [units: pascal]
p_e = 100e3    # Exit pressure [units: pascal]
gamma = 1.2    # Exhaust heat capacity ratio [units: dimensionless]
m_molar = 20e-3    # Exhaust molar mass [units: kilogram mole**1]
T_c = 3000.    # Chamber temperature [units: kelvin]

# Compute the exit velocity

v_e = isentropic.velocity(v_1=0, p_1=p_c, T_1=T_c, p_2=p_e, gamma=gamma, m_molar=m_molar)