Source code for aerosandbox.atmosphere.thermodynamics.choked_flow
import aerosandbox.numpy as np
from aerosandbox.atmosphere.thermodynamics.gas import universal_gas_constant
[docs]def mass_flow_rate(
mach,
area,
total_pressure,
total_temperature,
molecular_mass=28.9644e-3,
gamma=1.4,
):
specific_gas_constant = universal_gas_constant / molecular_mass
return (
(area * total_pressure) * (gamma / specific_gas_constant / total_temperature) ** 0.5
* mach * (1 + (gamma - 1) / 2 * mach ** 2) ** (- (gamma + 1) / (2 * (gamma - 1)))
)