[littlek]

Hey guys,

I’m trying to replicate the transonic, inviscid results of an inverse turbine blade design thesis. I have the original blade geometry, and have more or less copied the original mesh. The original geometry is discontinuous, leading to a passage shock at the discontinuity (I’ve attached geometry and Mach contour images). In the thesis, the ratio of back pressure to stagnation pressure is given as 0.65, so I’ve been using a pressure inlet and outlet and just picking pressures that correspond to that ratio. However, if I’m using lower pressures, i.e. Po = 100 kPa and Pback = 65 kPa, I don’t get a shock at all. As I increase both pressures (Po = 10 000 kPa, Pback = 6 500 kPa), I am getting the shock, but it’s upstream of the discontinuity (shown in the 3rd attached picture).

I’d really appreciate any advice as to what I can do to improve these results. Thanks.