aerosandbox.library.aerodynamics.normal_shock_relations
=======================================================

.. py:module:: aerosandbox.library.aerodynamics.normal_shock_relations


Functions
---------

.. autoapisummary::

   aerosandbox.library.aerodynamics.normal_shock_relations.mach_number_after_normal_shock
   aerosandbox.library.aerodynamics.normal_shock_relations.density_ratio_across_normal_shock
   aerosandbox.library.aerodynamics.normal_shock_relations.temperature_ratio_across_normal_shock
   aerosandbox.library.aerodynamics.normal_shock_relations.pressure_ratio_across_normal_shock
   aerosandbox.library.aerodynamics.normal_shock_relations.total_pressure_ratio_across_normal_shock
   aerosandbox.library.aerodynamics.normal_shock_relations.q_ratio


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

.. py:function:: mach_number_after_normal_shock(mach_upstream, gamma=1.4)

   Computes the mach number immediately after a normal shock wave.

   :param mach_upstream: The mach number immediately before the normal shock wave.
   :param gamma: The ratio of specific heats of the fluid. 1.4 for air.

   Returns: The mach number immediately after the normal shock wave.



.. py:function:: density_ratio_across_normal_shock(mach_upstream, gamma=1.4)

   Computes the ratio of fluid density across a normal shock.

   Specifically, returns: rho_after_shock / rho_before_shock

   :param mach_upstream: The mach number immediately before the normal shock wave.
   :param gamma: The ratio of specific heats of the fluid. 1.4 for air.

   Returns: rho_after_shock / rho_before_shock



.. py:function:: temperature_ratio_across_normal_shock(mach_upstream, gamma=1.4)

   Computes the ratio of fluid temperature across a normal shock.

   Specifically, returns: T_after_shock / T_before_shock

   :param mach_upstream: The mach number immediately before the normal shock wave.
   :param gamma: The ratio of specific heats of the fluid. 1.4 for air.

   Returns: T_after_shock / T_before_shock



.. py:function:: pressure_ratio_across_normal_shock(mach_upstream, gamma=1.4)

   Computes the ratio of fluid static pressure across a normal shock.

   Specifically, returns: P_after_shock / P_before_shock

   :param mach_upstream: The mach number immediately before the normal shock wave.
   :param gamma: The ratio of specific heats of the fluid. 1.4 for air.

   Returns: P_after_shock / P_before_shock



.. py:function:: total_pressure_ratio_across_normal_shock(mach_upstream, gamma=1.4)

   Computes the ratio of fluid total pressure across a normal shock.

   Specifically, returns: Pt_after_shock / Pt_before_shock

   :param mach_upstream: The mach number immediately before the normal shock wave.
   :param gamma: The ratio of specific heats of the fluid. 1.4 for air.

   Returns: Pt_after_shock / Pt_before_shock



.. py:function:: q_ratio(mach)