[icedevill]

Hi. I am currently trying to simulate the flow over a rae2822 aerofoil. This is a transonic flow and from what I've read in the forum one of the suggested solvers is sonicFoam. The mesh was build using gmsh and I've adapted the data in the 0 folder to best suit my configuration. The initial conditions are found http://www.grc.nasa.gov/WWW/wind/valid/raetaf/raetaf04/raetaf04.html . The problem is that my Cp pressure distribution is nothing near of the original experiment results. I have attached my 0, system and constant folder if this could help. Also i attached a chart of the distribution of the pressure. Thank you in advance