Software development for numeral modeling of hypersonic aerogasdynamics problem perspective aircrafts

In this paper effective computational techniques are described which are used in process of «Sigma» software development for provide in semi-aided mode of multidimensional non-stationary gas dynamics simulation in complex domain with curved boundary. The main algorithms for calculation mesh generation and numeral solution are parallel geometric algorithms and are realized for shared-memory supercomputers. Some results of axisymmetric and spatial flows in supersonic inlet and near boundaries of hypersonic aircraft are presented.