A computational study of a supersonic flow in the base region and the nearest wake of a cylindrical body moving at a supersonic speed has been carried out. In this case, the “prehistory” of the flow was taken into account, i.e. the configuration of the computational domain was as close as possible to the real one. The use of various RANS turbulence models for calculating flow in the base region and the nearest wake was analyzed. The following turbulence models were considered: 1) SST model; 2) Standard k–ε model; 3) k–ε RNG model; 4) Standard Reynolds Stress (RS) model; 5) RS BSL model. Based on a comparison of the calculation results with experimental data, it is shown that: 1) when calculating the flow in the base region and in the wake of the vehicle, it is very important to take into account the “prehistory” of the flow, i.e. to calculate the flow around the entire vehicle; 2) the best match was obtained using the the k–ε RNG model. The effect of base bleed on the near-wake flowfield of a cylindrical afterbody aligned with a Mach 2.5 flow has been investigated.

The complexity of problems in gas dynamics is increasing from year to year, which makes sequential computational codes more and more inadequate and brings the importance of creating their parallel implementations. The problem of building the parallel implementations is not simple, especially in case of parallelization of the existing sequential codes. In this paper we present a method of simulation of high-enthalpy flows and describe the peculiarities of its parallel implementation utilizing PETSc library, which gives a wide variety of tools to simplify creation of parallel codes. The results for calculation of OREX reentry module as well as analysis of scalability of the parallel code implementation are given.