From ce1b5d06c22b2e8a51464ad13cf291c5d88e1e42 Mon Sep 17 00:00:00 2001 From: Mikael Vaillant Date: Wed, 20 Nov 2024 14:10:22 -0500 Subject: [PATCH] Undo a modification in the documentation --- .../2d-naca0012-low-reynolds/2d-naca0012-low-reynolds.rst | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/doc/source/examples/incompressible-flow/2d-naca0012-low-reynolds/2d-naca0012-low-reynolds.rst b/doc/source/examples/incompressible-flow/2d-naca0012-low-reynolds/2d-naca0012-low-reynolds.rst index 50e981979c..c40a10d91e 100644 --- a/doc/source/examples/incompressible-flow/2d-naca0012-low-reynolds/2d-naca0012-low-reynolds.rst +++ b/doc/source/examples/incompressible-flow/2d-naca0012-low-reynolds/2d-naca0012-low-reynolds.rst @@ -28,7 +28,7 @@ All files mentioned below are located in the example's folder (``examples/incomp Description of the Case ----------------------- -In this example, a two-dimensional flow around a NACA airfoil is studied. According to Wikipedia, the *NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA)*. The NACA is the ancestor of the well-known `NASA `_. The airfoils, simply referred to as NACAs afterwards, can be described by a set of four parameters for the simpler airfoils, allowing the generation of a lot of different profiles. Since we deal with a symmetrical NACA we will only consider two of these four parameters, which describe the maximum thickness of the airfoil in percentage of the chord. The maximum camber and its position, are set to zero. The problem under study is presented in the figure below, which details the boundary conditions chosen and gives an idea of the size of the computational domain. +In this example, a two-dimensional flow around a NACA airfoil is studied. According to Wikipedia, the *NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA)*. The NACA is the ancestor of the well-known NASA _. The airfoils, simply referred to as NACAs afterwards, can be described by a set of four digits for the simpler airfoils, allowing the generation of a lot of different profiles. Since we deal with a symmetrical NACA we will only consider the last two digits, which describe the maximum thickness of the airfoil in percentage of the chord. The first two digits, describing the maximum camber and its position, are set to zero. The problem under study is presented in the figure below, which details the boundary conditions chosen and gives an idea of the size of the computational domain. .. image:: image/explanations_BC.png