nbsp

examples/laplace.markdown

@@ -195,22 +195,22 @@ wing has to satisfy the Kutta condition.
 
 This example
 
-1.  Creates a symmetric airfoil-like Joukowsky profile using the the
-    Gmsh Python API.
+1.  Creates a symmetric airfoil-like [Joukowsky profile] using the the
+    Gmsh Python API
 2.  Solves the steady-state 2D Laplace equation with a different
     Dirichlet value at the airfoil until the solution $\phi$ evaluated
     at the continuation of the wing tip matches the boundary value $c$.
     It then computes the circulation integral of the velocities
     1.  over the profile itself
     2.  over a circle around the airfoil, computing the unitary
         tangential vector
-        1.  from the internal normal variables `nx` and `ny`
-        2.  from two functions `tx` and `ty` using the circle’s equation
+        1.  from the internal normal variables `nx` and `ny`
+        2.  from two functions `tx` and `ty` using the circle’s equation
     3.  around the original rectangular domain
 
     It also computes the drag and the lift scalars as the integral of
-    the pressure (computed from Bernoulli’s principle) times `nx` and
-    `nz` over the circle, respectively.
+    the pressure (computed from Bernoulli’s principle) times `nx`
+    and `nz` over the circle, respectively.
 
 <figure>
 <img src="airfoil-msh1.png" style="width:100.0%" alt="Full domain" />
@@ -482,3 +482,5 @@ alt="Potential and velocities zoomed over the airfoil" />
 <figcaption aria-hidden="true">Potential and velocities zoomed over the
 airfoil</figcaption>
 </figure>
+
+  [Joukowsky profile]: https://en.wikipedia.org/wiki/Joukowsky_transform

examples/laplace.md

@@ -179,22 +179,23 @@ wing has to satisfy the Kutta condition.
 
 This example
 
-1.  Creates a symmetric airfoil-like Joukowsky profile using the the
-    Gmsh Python API.
+1.  Creates a symmetric airfoil-like [Joukowsky
+    profile](https://en.wikipedia.org/wiki/Joukowsky_transform) using
+    the the Gmsh Python API
 2.  Solves the steady-state 2D Laplace equation with a different
     Dirichlet value at the airfoil until the solution $\phi$ evaluated
     at the continuation of the wing tip matches the boundary value $c$.
     It then computes the circulation integral of the velocities
     a.  over the profile itself
     b.  over a circle around the airfoil, computing the unitary
         tangential vector
-        i.  from the internal normal variables `nx` and `ny`
-        ii. from two functions `tx` and `ty` using the circle's equation
+        i.  from the internal normal variables `nx` and `ny`
+        ii. from two functions `tx` and `ty` using the circle's equation
     c.  around the original rectangular domain
 
     It also computes the drag and the lift scalars as the integral of
-    the pressure (computed from Bernoulli's principle) times `nx` and
-    `nz` over the circle, respectively.
+    the pressure (computed from Bernoulli's principle) times `nx`
+    and `nz` over the circle, respectively.
 
 ![Full domain](airfoil-msh1.png){width="100%"}