SIMULATION OF SUPERSONIC FLOWS ON THE BASIS OF SPLITTING ALGORITHMS

For the numerical simulation of aerodynamics problems, the Euler and Navier - Stokes equations written in integral form are used to construct an implicit finite-volume predictor-corrector scheme. At the predictor stage, the splitting of equations into physical processes and spatial directions is introduced, which makes it possible to reduce the solution of the original system to the solution of individual equations on fractional steps by the scalar sweep method and ensure the stability of the algorithm as a whole. The paper also describes the supersonic gas flows in a narrowing channel with regular and non-regular reflection of the compression shock from the symmetry plane and the numerical substantiation of the existence of pulsating flow with a supersonic flow past a cylinder with a needle.