nacaAirfoil
~~~~~~~~~~~
* large domain with airfoil section near centre
* extremely non-orthogonal, highly skew mesh refined around the airfoil
* running at Mach 1.78 
* run with Gamma schemes for U, p and h div terms, upwind on rest
* limited 0.5 on all laplacianSchemes because the mesh is so poor
* run to t = 0.02 with nextWrite; change to stopAt endTime to continue running 
* deltaT can be increased later in the run to 2e-07 

prism
~~~~~
* run to t = 0.0014 for convergence 
