aerosandbox.library.aerodynamics.inviscid
=========================================

.. py:module:: aerosandbox.library.aerodynamics.inviscid


Attributes
----------

.. autoapisummary::

   aerosandbox.library.aerodynamics.inviscid.machs


Functions
---------

.. autoapisummary::

   aerosandbox.library.aerodynamics.inviscid.induced_drag
   aerosandbox.library.aerodynamics.inviscid.oswalds_efficiency
   aerosandbox.library.aerodynamics.inviscid.optimal_taper_ratio
   aerosandbox.library.aerodynamics.inviscid.CL_over_Cl
   aerosandbox.library.aerodynamics.inviscid.induced_drag_ratio_from_ground_effect


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

.. py:function:: induced_drag(lift, span, dynamic_pressure, oswalds_efficiency=1)

   Computes the induced drag associated with a lifting planar wing.

   :param lift: Lift force [Newtons]
   :param span: Wing span [meters]
   :param dynamic_pressure: Dynamic pressure [Pascals]
   :param oswalds_efficiency: Oswald's efficiency factor [-]

   Returns: Induced drag force [Newtons]



.. py:function:: oswalds_efficiency(taper_ratio, aspect_ratio, sweep = 0.0, fuselage_diameter_to_span_ratio = 0.0, method='nita_scholz')

   Computes the Oswald's efficiency factor for a planar, tapered, swept wing.

   Based on "Estimating the Oswald Factor from Basic Aircraft Geometrical Parameters"
   by M. Nita, D. Scholz; Hamburg Univ. of Applied Sciences, 2012.
   https://www.fzt.haw-hamburg.de/pers/Scholz/OPerA/OPerA_PUB_DLRK_12-09-10.pdf

   Implementation of Section 5 from the above paper.

   Only valid for backwards-swept wings; i.e. 0 <= sweep < 90.

   :param taper_ratio: Taper ratio of the wing (tip_chord / root_chord) [-]
   :param aspect_ratio: Aspect ratio of the wing (b^2 / S) [-]
   :param sweep: Wing quarter-chord sweep angle [deg]

   Returns: Oswald's efficiency factor [-]



.. py:function:: optimal_taper_ratio(sweep=0.0)

   Computes the optimal (minimum-induced-drag) taper ratio for a given quarter-chord sweep angle.

   Based on "Estimating the Oswald Factor from Basic Aircraft Geometrical Parameters"
   by M. Nita, D. Scholz; Hamburg Univ. of Applied Sciences, 2012.

   Only valid for backwards-swept wings; i.e. 0 <= sweep < 90.

   :param sweep: Wing quarter-chord sweep angle [deg]

   Returns: Optimal taper ratio



.. py:function:: CL_over_Cl(aspect_ratio, mach = 0.0, sweep = 0.0, Cl_is_compressible = True)

   Returns the ratio of 3D lift coefficient (with compressibility) to the 2D lift coefficient.

   Specifically: CL_3D / CL_2D

   :param aspect_ratio: The aspect ratio of the wing.
   :param mach: The freestream Mach number.
   :param sweep: The sweep of the wing, in degrees. To be most accurate, this should be the sweep at the locus of
   :param thickest points along the wing.:
   :param Cl_is_compressible: This flag indicates whether the 2D airfoil data already has compressibility effects
   :param modeled.:
                    For example:

                        * If this flag is True, this function returns: CL_3D / CL_2D, where CL_2D is the sectional lift
                        coefficient based on the local profile at the freestream mach number.

                        * If this flag is False, this function returns: CL_3D / CL_2D_at_mach_zero, where CL_2D_... is the
                        sectional lift coefficient based on the local profile at mach zero.

                    For most accurate results, set this flag to True, and then model profile characteristics separately.


.. py:function:: induced_drag_ratio_from_ground_effect(h_over_b)

   Gives the ratio of actual induced drag to free-flight induced drag experienced by a wing in ground effect.
   Artificially smoothed below around h/b == 0.05 to retain differentiability and practicality.
   Source: W. F. Phillips, D. F. Hunsaker, "Lifting-Line Predictions for Induced Drag and Lift in Ground Effect".
       Using Equation 5 from the paper, which is modified from a model from Torenbeek:
           Torenbeek, E. "Ground Effects", 1982.
   :param h_over_b: (Height above ground) divided by (wingspan).
   :return: Ratio of induced drag in ground effect to induced drag out of ground effect [unitless]


.. py:data:: machs