CompAero/IsentropecRelations.py
def calc_mach_from_T0_T(t0_t: float, gamma: float) -> float:
        """Calculates the Mach number for a flow given the ratio of total temperature to static temperature

        Args:
            t0_t (float): Ratio of total temperature to static temperature
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        """
        return sqrt((t0_t - 1) * 2 / (gamma - 1))
Calculates the Mach number for a flow given the ratio of total temperature to static temperature

        Args:
            t0_t (float): Ratio of total temperature to static temperature
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        
Calculates the Mach number for a flow given the ratio of total temperature to static temperature
Calculates the Mach number for a flow given the ratio of total temperature to static temperature
def calc_mach_from_T0_T(t0_t: float, gamma: float) -> float:
        return sqrt((t0_t - 1) * 2 / (gamma - 1))
def calc_mach_from_T0_T ( t0_t : float , gamma : float ) -> float : return sqrt ( ( t0_t - 1 ) * 2 / ( gamma - 1 ) )
Calculates the Mach number for a flow given the ratio of total temperature to static temperature
Calculates the Mach number for a flow given the ratio of total temperature to static temperature
"""Calculates the Mach number for a flow given the ratio of total temperature to static temperature

        Args:
            t0_t (float): Ratio of total temperature to static temperature
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        """
None
float
t0_t
float
Ratio of total temperature to static temperature
Ratio of total temperature to static temperature
gamma
float
ratio of specific heats
ratio of specific heats