CompAero/RayleighFlowRelations.py
def calc_mach_from_P_PStar(p_pSt: float, gamma: float) -> float:
        """Calculates the mach number based of the ratio of static pressure to sonic static pressure P/P*

        Args:
            p_pSt (float): Ratio of static pressure to sonic static pressure P/P*
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        """
        return brenth(RayleighFlowRelations.calc_P_Pstar, 1e-9, 40, args=(gamma, p_pSt,))
Calculates the mach number based of the ratio of static pressure to sonic static pressure P/P*

        Args:
            p_pSt (float): Ratio of static pressure to sonic static pressure P/P*
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        
Calculates the mach number based of the ratio of static pressure to sonic static pressure P/P
Calculates the mach number based of the ratio of static pressure to sonic static pressure P / P
def calc_mach_from_P_PStar(p_pSt: float, gamma: float) -> float:
        return brenth(RayleighFlowRelations.calc_P_Pstar, 1e-9, 40, args=(gamma, p_pSt,))
def calc_mach_from_P_PStar ( p_pSt : float , gamma : float ) -> float : return brenth ( RayleighFlowRelations . calc_P_Pstar , 1e-9 , 40 , args = ( gamma , p_pSt , ) )
Calculates the mach number based of the ratio of static pressure to sonic static pressure P/P
Calculates the mach number based of the ratio of static pressure to sonic static pressure P / P
"""Calculates the mach number based of the ratio of static pressure to sonic static pressure P/P*

        Args:
            p_pSt (float): Ratio of static pressure to sonic static pressure P/P*
            gamma (float): ratio of specific heats

        Returns:
            float: mach number
        """
None
float
p_pSt
float
Ratio of static pressure to sonic static pressure P/P
Ratio of static pressure to sonic static pressure P / P
gamma
float
ratio of specific heats
ratio of specific heats