Fixed headings

README.md

@@ -1,11 +1,9 @@
-AirfoilMesh
-=================================================================
+# AirfoilMesh
 A Glyph script for generating NACA 4-series airfoil geometries and boundary layer meshes.
 
 ![AirfoilMeshGUI](https://raw.github.com/pointwise/AirfoilMesh/master/ScriptImage.png)
 
-Generating or Importing Geometry
---------------------------------
+## Generating or Importing Geometry
 This script provides a way to generate NACA 4-Series airfoil geometries within Pointwise without relying on external coordinate files. Simply input the 4 digits defining a NACA 4-Series airfoil and click CREATE. However, the script does support the ability to import external airfoil coordinates from a segment file. The only requirement is that the airfoil should consist of three segments, the upper surface, lower surface, and trailing edge. In the current implementation, this script only handles airfoils with a finite trailing edge.
 
 ### NACA 4-Series Geometry Description
@@ -24,8 +22,7 @@ This script provides a way to generate NACA 4-Series airfoil geometries within P
 * Maximum camber located at 40% of the chord
 * Maximum thickness is 12% of the chord (located at 30% of the chord)
 
-Boundary Layer Meshing
-----------------------
+## Boundary Layer Meshing
 This script also automates the mesh generation process within Pointwise by asking the user to provide common boundary layer parameters. Assuming a unit length for the airfoil, the parameters are factors of the chord length. Once the boundary layer parameters have been selected, click MESH to generate a high quality structured O-grid topology using Pointwise's normal hyperbolic extrusion tool. Note that while the user has the ability to adjust common boundary layer parameters, more advanced parameters can be found within the attached Glyph script.  
 
 ### Boundary layer parameters
@@ -34,8 +31,7 @@ This script also automates the mesh generation process within Pointwise by askin
 * The maximum boundary layer distance
 * The number of points around the airfoil, excluding the trailing edge
 
-Disclaimer
-----------
+## Disclaimer
 Scripts are freely provided. They are not supported products of Pointwise, Inc. Some scripts have been written and contributed by third parties outside of Pointwise's control.
 
 TO THE MAXIMUM EXTENT PERMITTED BY APPLICABLE LAW, POINTWISE DISCLAIMS ALL WARRANTIES, EITHER EXPRESS OR IMPLIED, INCLUDING, BUT NOT LIMITED TO, IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE, WITH REGARD TO THESE SCRIPTS. TO THE MAXIMUM EXTENT PERMITTED BY APPLICABLE LAW, IN NO EVENT SHALL POINTWISE BE LIABLE TO ANY PARTY FOR ANY SPECIAL, INCIDENTAL, INDIRECT, OR CONSEQUENTIAL DAMAGES WHATSOEVER (INCLUDING, WITHOUT LIMITATION, DAMAGES FOR LOSS OF BUSINESS INFORMATION, OR ANY OTHER PECUNIARY LOSS) ARISING OUT OF THE USE OF OR INABILITY TO USE THESE SCRIPTS EVEN IF POINTWISE HAS BEEN ADVISED OF THE POSSIBILITY OF SUCH DAMAGES AND REGARDLESS OF THE FAULT OR NEGLIGENCE OF POINTWISE.