aerosandbox.atmosphere.thermodynamics.isentropic_flow
=====================================================

.. py:module:: aerosandbox.atmosphere.thermodynamics.isentropic_flow


Attributes
----------

.. autoapisummary::

   aerosandbox.atmosphere.thermodynamics.isentropic_flow.mach


Functions
---------

.. autoapisummary::

   aerosandbox.atmosphere.thermodynamics.isentropic_flow.temperature_over_total_temperature
   aerosandbox.atmosphere.thermodynamics.isentropic_flow.pressure_over_total_pressure
   aerosandbox.atmosphere.thermodynamics.isentropic_flow.density_over_total_density
   aerosandbox.atmosphere.thermodynamics.isentropic_flow.area_over_choked_area


Module Contents
---------------

.. py:function:: temperature_over_total_temperature(mach, gamma=1.4)

   Gives T/T_t, the ratio of static temperature to total temperature.

   :param mach: Mach number [-]
   :param gamma: The ratio of specific heats. 1.4 for air across most temperature ranges of interest.


.. py:function:: pressure_over_total_pressure(mach, gamma=1.4)

   Gives P/P_t, the ratio of static pressure to total pressure.

   :param mach: Mach number [-]
   :param gamma: The ratio of specific heats. 1.4 for air across most temperature ranges of interest.


.. py:function:: density_over_total_density(mach, gamma=1.4)

   Gives rho/rho_t, the ratio of density to density after isentropic compression.

   :param mach: Mach number [-]
   :param gamma: The ratio of specific heats. 1.4 for air across most temperature ranges of interest.


.. py:function:: area_over_choked_area(mach, gamma=1.4)

   Gives A/A^* (where A^* is "A-star"), the ratio of cross-sectional flow area to the cross-sectional flow area that would result in choked (M=1) flow.

   Applicable to 1D isentropic nozzle flow.

   :param mach: Mach number [-]
   :param gamma: The ratio of specific heats. 1.4 for air across most temperature ranges of interest.


.. py:data:: mach