The Numerical Simulation Supersonic Flows over Complex Shaped Bodies

A series of numerical and experimental studies was performed to reveal the flow pattern in the region between separating winged stages of promising aerospace systems. Surface pressure distributions and visualization of interacting shock waves were obtained for sertain range of relative positions of the stages and angles of attack for M=3. The comparison between experimental and numerical data is discussed. The algorithm for numerical simulation of supersonic flows over complex shaped bodies within the framework of the steady Euler equations is presented.. Block structured grids are used. To achieve higher accuracy of Godunov scheme the piecewise linear distributions of flow variables are used. The parallel implementation of steady Euler solver on the multiprocessor system is discussed. The results of experimental studies forms the basis for verification and improvement of the numerical method.