aerosandbox.library.propulsion_turbofan
=======================================

.. py:module:: aerosandbox.library.propulsion_turbofan


Attributes
----------

.. autoapisummary::

   aerosandbox.library.propulsion_turbofan.atmo


Functions
---------

.. autoapisummary::

   aerosandbox.library.propulsion_turbofan.thrust_turbofan
   aerosandbox.library.propulsion_turbofan.thrust_specific_fuel_consumption_turbofan
   aerosandbox.library.propulsion_turbofan.mass_turbofan
   aerosandbox.library.propulsion_turbofan.m_dot_corrected_over_m_dot


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

.. py:function:: thrust_turbofan(mass_turbofan)

   Estimates the maximum rated dry thrust of a turbofan engine. A regression to historical data.

   Based on data for both civilian and military turbofans, available in:
   `aerosandbox/library/datasets/turbine_engines/data.xlsx`

   Applicable to both turbojets and turbofans, and with sizes ranging from micro-turbines (<1 kg) to large transport
   aircraft turbofans.

   See studies in `/AeroSandbox/studies/TurbofanStudies/make_fit_thrust.py` for model details.

   :param mass_turbofan: The mass of the turbofan engine. [kg]

   :returns: The maximum (rated takeoff) dry thrust of the turbofan engine. [N]


.. py:function:: thrust_specific_fuel_consumption_turbofan(mass_turbofan, bypass_ratio)

   Estimates the thrust-specific fuel consumption (TSFC) of a turbofan engine. A regression to historical data.

   Based on data for both civilian and military turbofans, available in:
   `aerosandbox/library/datasets/turbine_engines/data.xlsx`

   Applicable to both turbojets and turbofans, and with sizes ranging from micro-turbines (<1 kg) to large transport
   aircraft turbofans.

   See studies in `/AeroSandbox/studies/TurbofanStudies/make_fit_tsfc.py` for model details.



.. py:function:: mass_turbofan(m_dot_core_corrected, overall_pressure_ratio, bypass_ratio, diameter_fan)

   Computes the combined mass of a bare turbofan, nacelle, and accessory and pylon weights.

   Bare weight depends on m_dot, OPR, and BPR.

   Nacelle weight is a function of various areas and fan diameter.

   From TASOPT documentation by Mark Drela, available here: http://web.mit.edu/drela/Public/web/tasopt/TASOPT_doc.pdf
       Section: "Turbofan Weight Model from Historical Data"

   :param m_dot_core_corrected: The mass flow of the core only, corrected to standard conditions. [kg/s]
   :param overall_pressure_ratio: The overall pressure ratio (OPR) [-]
   :param bypass_ratio: The bypass ratio (BPR) [-]
   :param diameter_fan: The diameter of the fan. [m]

   Returns: The total engine mass. [kg]



.. py:function:: m_dot_corrected_over_m_dot(temperature_total_2, pressure_total_2)

   Computes the ratio `m_dot_corrected / m_dot`, where:

       * `m_dot_corrected` is the corrected mass flow rate, where corrected refers to correction to ISO 3977 standard
       temperature and pressure conditions (15C, 101325 Pa).

       * `m_dot` is the raw mass flow rate, at some other conditions.

   :param temperature_total_2: The total temperature at the compressor inlet face, at the conditions to be evaluated. [K]
   :param pressure_total_2: The total pressure at the compressor inlet face, at the conditions to be evaluated. [Pa]

   :returns: The ratio `m_dot_corrected / m_dot`.


.. py:data:: atmo