CompAero/IsentropecRelations.py
def calc_mach_from_p0_p(p0_p: float, gamma: float) -> float:
        """Calculates the Mach number for a flow given the ratio of total pressure to static pressure

        Args:
            p0_p (float): Ratio of total pressure to static pressure
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        """

        return brenth(IsentropicRelations.calc_P0_P, 0, 30, args=(gamma, p0_p))
Calculates the Mach number for a flow given the ratio of total pressure to static pressure

        Args:
            p0_p (float): Ratio of total pressure to static pressure
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        
Calculates the Mach number for a flow given the ratio of total pressure to static pressure
Calculates the Mach number for a flow given the ratio of total pressure to static pressure
def calc_mach_from_p0_p(p0_p: float, gamma: float) -> float:
        return brenth(IsentropicRelations.calc_P0_P, 0, 30, args=(gamma, p0_p))
def calc_mach_from_p0_p ( p0_p : float , gamma : float ) -> float : return brenth ( IsentropicRelations . calc_P0_P , 0 , 30 , args = ( gamma , p0_p ) )
Calculates the Mach number for a flow given the ratio of total pressure to static pressure
Calculates the Mach number for a flow given the ratio of total pressure to static pressure
"""Calculates the Mach number for a flow given the ratio of total pressure to static pressure

        Args:
            p0_p (float): Ratio of total pressure to static pressure
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        """
None
float
p0_p
float
Ratio of total pressure to static pressure
Ratio of total pressure to static pressure
gamma
float
ratio of specific heats
ratio of specific heats