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Numerical technology for fast and correct computation of non-stationary viscid gas flows is presented. It consists in the use of explicit numerical scheme with fractional time stepping and “wall law” boundary condition at the solid surfaces. The technology is verified by comparison with the calculation based on the no-slip boundary condition. Using this technology, the physics of supersonic flow in a model duct with combustion of hydrocarbon fuel in pseudoshock is analyzed. [ABSTRACT FROM AUTHOR]

Pulse detonation is a possible efficient way of combustion realization in various energetic devices. An original variant of pulse detonation engine of valveless scheme is considered. The aim is to investigate the possible effect of viscosity on the performance of pulse detonation engine. The problem is studied on the basis of numerical simulation. Two calculations of working process in pulse detonation engine are compared: with slipping boundary condition at all solid surfaces and taking into account the boundary layers. Analysis of physical features in both calculations is given. Strong influence of boundary layers on the damping device performance is revealed. It is shown that viscid effects may essentially deteriorate the pulse detonation engine performance. [ABSTRACT FROM AUTHOR]

Abstract Fast technologies for numerical simulation of high-speed flows in ducts, developed in TsAGI, are described. The examples are presented of the application of experimental data, obtained at T-131 wind tunnel, for validation of the developed numerical technologies: 1) validation of 2.5D and 3D calculations of flow in the elliptic combustor with hydrogen supersonic combustion that was studied within HEXAFLY-INT international project; 2) validation of 2D and 2.5D calculations of flow in high-speed model combustor duct with step-like expansion. Preparation of new series of experiments, oriented on validation of turbulent combustion models, is described. [ABSTRACT FROM AUTHOR]