Using blastFoam to simulate hypersonic shock-wave turbulent boundary layer interaction flow

Following selection to the Team Hypersonics UK Framework, we have been using blastFoam to simulate hypersonic shock-wave turbulent boundary layer interaction flow.

Experiments to characterize the flow field resulting from the interaction of a shock wave with a nonadiabatic hypersonic turbulent boundary layer were performed at the NASA Ames Research Center.

The test model consisted of a cone-ogive cylinder with an annular shock-wave generator mounted concentric with the cylinder.

Two shock wave strengths were imposed by beveling the leading edge of the generator at 7.5º (Mach 6.71) and 15º (Mach 6.86) resulting in unseparated and separated turbulent boundary layers, respectively.

Comparison simulations were conducted with the blastFoam solver using a 2D/Axisymmetric grid of 400 x 1000 cells.

Still free, still open source, still awesome. See for yourself: https://github.com/synthetik-technologies/blastfoam