Coupled gas heat and mass transfer problem solution using fully implicit method on graphics processing units

We present benchmarking results from a solver for hypersonic flow problems. The aim of the work is to verify new numerical methods designed for solving coupled heat and mass transfer problem with explicit or implicit time marching schemes using multiple graphics processing units and central processing units hybrid computational architecture without any usage of ANSYS Fluent. The verification is performed on the problem of a flow over the sphere. We consider hypersonic flow regimes of Mach number M = 20-30. New results are compared with results of the previous version of the code, where ANSYS Fluent was used to solve body heat and ablation problems. We consider the body shape after surface ablation, heat loads on the surface and aerodynamic loads on the whole sphere. We also compare timings between ANSYS Fluent and new heat and mass solver; compare time difference between explicit and implicit methods for gas dynamics part and present total wall time for convergence using different methods.