Isentropic Equations

turbodesign.isentropic.A_As(M: float | ndarray[tuple[Any, ...], dtype[float64]], gamma: float) → float | ndarray[tuple[Any, ...], dtype[float64]][source]

Computes the ratio of Area to Throat Area give a given mach number and gamma

Parameters:

  • M (np.ndarray) – Mach Number

  • gamma (float) – Specific Heat Ratio

Returns:

Area to throat area ratio

Return type:

float

turbodesign.isentropic.FindMachP0P(P0_P: float | ndarray[tuple[Any, ...], dtype[float64]], gamma: float) → float | ndarray[tuple[Any, ...], dtype[float64]][source]

Finds the mach number given a P0/P ratio

Parameters:

  • P0_P (np.ndarray) – ratio of total to static pressure

  • gamma (float) – specific heat ratio

Returns:

[description]

Return type:

float

turbodesign.isentropic.IsenP(M: float | ndarray[tuple[Any, ...], dtype[float64]], gamma: float) → float | ndarray[tuple[Any, ...], dtype[float64]][source]

Computes the ratio P0/Ps

Parameters:

  • M (np.ndarray) – Mach Number

  • gamma (float) – specific heat ratio

Returns:

P0/P ratio

Return type:

float

turbodesign.isentropic.IsenT(M: float | ndarray[tuple[Any, ...], dtype[float64]], gamma: float) → float | ndarray[tuple[Any, ...], dtype[float64]][source]

Computes T0/Ts

Parameters:

  • M (np.ndarray) – _description_

  • gamma (float) – _description_

Returns:

Ratio of T0/Ts

Return type:

float

turbodesign.isentropic.Massflow(P0: float | ndarray[tuple[Any, ...], dtype[float64]], T0: float | ndarray[tuple[Any, ...], dtype[float64]], A: float | ndarray[tuple[Any, ...], dtype[float64]], M: float | ndarray[tuple[Any, ...], dtype[float64]], gamma: float, R: float = 287) → float | ndarray[tuple[Any, ...], dtype[float64]][source]

Massflow rate calculation

Parameters:

  • P0 (float) – Inlet Total Pressure (Pa)

  • T0 (float) – Inlet Total Temperature (K)

  • A (float) – Area (m^2)

  • M (float) – Mach Number

  • gamma (float) – Ratio of specific heats

  • R (float) – Ideal Gas Constant. Defaults to 287 J/(KgK).

Returns:

Nusselt Number

Return type:

float

turbodesign.isentropic.solve_for_mach(M: float, massflow: float, P0: float, T0: float, area: float, gamma: float, R: float) → float[source]

Residual between desired and estimated massflow for a guessed Mach number.

Parameters:

  • M (float) – Mach number guess (dimensionless).

  • massflow (float) – Target massflow [kg/s].

  • P0 (float) – Total pressure [Pa].

  • T0 (float) – Total temperature [K].

  • area (float) – Flow area [m^2].

  • gamma (float) – Specific heat ratio Cp/Cv [-].

  • R (float) – Gas constant [J/(kg·K)].

Returns:

Absolute massflow residual [kg/s].

Return type:

float