CompAero/IsentropecRelations.py
def calc_A_Astar(mach: float, gamma: float, offset: float = 0.0) -> float:
        """Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)

        Args:
            mach (float): mach number of the flow
            gamma (float): ratio of specific heats
            offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0.

        Returns:
            float: A/A*
        """

        gm1 = gamma - 1
        gp1 = gamma + 1
        mSqr = pow(mach, 2)

        nonRaised = 2 / gp1 * (1 + gm1 / 2 * mSqr)

        return sqrt(pow(nonRaised, gp1 / gm1) / mSqr) - offset
Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)

        Args:
            mach (float): mach number of the flow
            gamma (float): ratio of specific heats
            offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0.

        Returns:
            float: A/A*
        
Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)
Calculates the ratio of Nozzle Area to Sonic Throat Area ( A / A * )
def calc_A_Astar(mach: float, gamma: float, offset: float = 0.0) -> float:
        gm1 = gamma - 1
        gp1 = gamma + 1
        mSqr = pow(mach, 2)
        nonRaised = 2 / gp1 * (1 + gm1 / 2 * mSqr)
        return sqrt(pow(nonRaised, gp1 / gm1) / mSqr) - offset
def calc_A_Astar ( mach : float , gamma : float , offset : float = 0.0 ) -> float : gm1 = gamma - 1 gp1 = gamma + 1 mSqr = pow ( mach , 2 ) nonRaised = 2 / gp1 * ( 1 + gm1 / 2 * mSqr ) return sqrt ( pow ( nonRaised , gp1 / gm1 ) / mSqr ) - offset
Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)
Calculates the ratio of Nozzle Area to Sonic Throat Area ( A / A * )
"""Calculates the ratio of Nozzle Area to Sonic Throat Area (A/A*)

        Args:
            mach (float): mach number of the flow
            gamma (float): ratio of specific heats
            offset (float, optional): offset that can be used for root finding for a specific value. Defaults to 0.0.

        Returns:
            float: A/A*
        """
None
float
mach
float
mach number of the flow
mach number of the flow
gamma
float
ratio of specific heats
ratio of specific heats
offset
float
offset that can be used for root finding for a specific value. Defaults to 0.0.
offset that can be used for root finding for a specific value . Defaults to 0 . 0 .
0.0