.. _sphx_glr_api_gallery_aerodynamics_airfoils:

Airfoils
--------

NACA four-digit section geometry and thin-airfoil theory.


.. raw:: html

  <div id='sg-tag-list' class='sphx-glr-tag-list'></div>


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    <div class="sphx-glr-thumbnails">

.. thumbnail-parent-div-open

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    <div class="sphx-glr-thumbcontainer" tooltip="In NACA Report 460 (1933) Eastman Jacobs and colleagues tested 78 related sections in the variable-density tunnel. Each is defined by a single thickness polynomial wrapped around a two-parabola camber line, so four digits specify the whole shape: 2412 has 2% camber at 40% chord and is 12% thick. naca4_airfoil builds the coordinates; summary recovers the digits from the geometry.">

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  .. image:: /api/gallery/aerodynamics/airfoils/images/thumb/sphx_glr_plot_01_naca_four_digit_sections_thumb.png
    :alt:

  :doc:`/api/gallery/aerodynamics/airfoils/plot_01_naca_four_digit_sections`

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      <div class="sphx-glr-thumbnail-title">The NACA four-digit airfoil family</div>
    </div>


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    <div class="sphx-glr-thumbcontainer" tooltip="Max Munk (1922) and Hermann Glauert (1926) replaced a thin section by a vortex sheet on its camber line. Satisfying flow tangency gives a lift slope of exactly 2\pi per radian for every thin section, while camber only shifts the curve by a zero-lift angle given by an integral of the camber slope. naca4_zero_lift_angle evaluates that integral for NACA four-digit camber lines, and thin_airfoil_cl gives the lift line.">

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  .. image:: /api/gallery/aerodynamics/airfoils/images/thumb/sphx_glr_plot_02_thin_airfoil_theory_thumb.png
    :alt:

  :doc:`/api/gallery/aerodynamics/airfoils/plot_02_thin_airfoil_theory`

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      <div class="sphx-glr-thumbnail-title">Thin-airfoil theory: lift slope 2π and the camber shift</div>
    </div>


.. thumbnail-parent-div-close

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    </div>


.. toctree::
   :hidden:

   /api/gallery/aerodynamics/airfoils/plot_01_naca_four_digit_sections
   /api/gallery/aerodynamics/airfoils/plot_02_thin_airfoil_theory