aerosandbox.library.aerodynamics.transonic
==========================================

.. py:module:: aerosandbox.library.aerodynamics.transonic


Attributes
----------

.. autoapisummary::

   aerosandbox.library.aerodynamics.transonic.mc


Functions
---------

.. autoapisummary::

   aerosandbox.library.aerodynamics.transonic.sears_haack_drag
   aerosandbox.library.aerodynamics.transonic.sears_haack_drag_from_volume
   aerosandbox.library.aerodynamics.transonic.mach_crit_Korn
   aerosandbox.library.aerodynamics.transonic.Cd_wave_Korn
   aerosandbox.library.aerodynamics.transonic.approximate_CD_wave


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

.. py:function:: sears_haack_drag(radius_max, length)

   Yields the idealized drag area (denoted CDA, or equivalently, D/q) of a Sears-Haack body.

   Assumes linearized supersonic (Prandtl-Glauert) flow.

   https://en.wikipedia.org/wiki/Sears%E2%80%93Haack_body

   Note that drag coefficient and drag area are independent of Mach number for this case (assuming linearized supersonic aero).

   :param radius_max: The maximum radius of the Sears-Haack body.
   :param length: The length of the Sears-Haack body.

   Returns: The drag area (CDA, or D/q) of the body. To get the drag force, multiply by the dynamic pressure.



.. py:function:: sears_haack_drag_from_volume(volume, length)

   See documentation for sears_haack_drag() in this same file.

   Identical, except takes volume as an input rather than max radius.

   Also returns a drag area (denoted CDA, or equivalently, D/q).


.. py:function:: mach_crit_Korn(CL, t_over_c, sweep=0, kappa_A=0.95)

       Wave drag_force coefficient prediction using the low-fidelity Korn Equation method;
   derived in "Configuration Aerodynamics" by W.H. Mason, Sect. 7.5.2, pg. 7-18

   :param CL: Sectional lift coefficient
   :param t_over_c: thickness-to-chord ratio
   :param sweep: sweep angle, in degrees
   :param kappa_A: Airfoil technology factor (0.95 for supercritical section, 0.87 for NACA 6-series)

   Returns:



.. py:function:: Cd_wave_Korn(Cl, t_over_c, mach, sweep=0, kappa_A=0.95)

   Wave drag_force coefficient prediction using the low-fidelity Korn Equation method;
   derived in "Configuration Aerodynamics" by W.H. Mason, Sect. 7.5.2, pg. 7-18

   :param Cl: Sectional lift coefficient
   :param t_over_c: thickness-to-chord ratio
   :param sweep: sweep angle, in degrees
   :param kappa_A: Airfoil technology factor (0.95 for supercritical section, 0.87 for NACA 6-series)
   :return: Wave drag coefficient


.. py:function:: approximate_CD_wave(mach, mach_crit, CD_wave_at_fully_supersonic)

   An approximate relation for computing transonic wave drag, based on an object's Mach number.

   Considered reasonably valid from Mach 0 up to around Mach 2 or 3-ish.

   Methodology is a combination of:

       * The methodology described in Raymer, "Aircraft Design: A Conceptual Approach", Section 12.5.10 Transonic Parasite Drag (pg. 449 in Ed. 2)

       and

       * The methodology described in W.H. Mason's Configuration Aerodynamics, Chapter 7. Transonic Aerodynamics of Airfoils and Wings.

   :param mach: Mach number at the operating point to be evaluated
   :param mach_crit: Critical mach number, a function of the body geometry
   :param CD_wave_at_fully_supersonic: The wave drag coefficient of the body at the speed that it first goes (
   :param effectively) fully supersonic.: Here, that is taken to mean at the Mach 1.2 case.

                                          This value should probably be derived using something similar to a Sears-Haack relation for the body in
                                          question, with a markup depending on geometry smoothness.

                                          The CD_wave predicted by this function will match this value exactly at M=1.2 and M=1.05.

                                          The peak CD_wave that is predicted is ~1.23 * this value, which occurs at M=1.10.

                                          In the high-Mach limit, this function asymptotes at 0.80 * this value, as empirically stated by Raymer.
                                          However, this model is only approximate and is likely not valid for high-supersonic flows.

   Returns: The approximate wave drag coefficient at the specified Mach number.

       The reference area is whatever the reference area used in the `CD_wave_at_fully_supersonic` parameter is.



.. py:data:: mc
   :value: 0.6