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We consider a one-dimensional three velocity kinetic lattice Boltzmann model, which represents a secondorder difference scheme for hydrodynamic equations. In the framework of kinetic theory this system describes the propagation and interaction of three types of particles. It has been shown previously that the lattice Boltzmann model with external virtual force is equivalent at the hydrodynamic limit to the one-dimensional hemodynamic equations for elastic vessels, this equivalence can be achieved with use of the Chapman – Enskog expansion. The external force in the model is responsible for the ability to adjust the functional dependence between the lumen area of the vessel and the pressure applied to the wall of the vessel under consideration. Thus, the form of the external force allows to model various elastic properties of the vessels. In the present paper the physiological boundary conditions are considered at the inlets and outlets of the arterial network in terms of the lattice Boltzmann variables. We consider the following boundary conditions: for pressure and blood flow at the inlet of the vascular network, boundary conditions for pressure and blood flow for the vessel bifurcations, wave reflection conditions (correspond to complete occlusion of the vessel) and wave absorption at the ends of the vessels (these conditions correspond to the passage of the wave without distortion), as well as RCR-type conditions, which are similar to electrical circuits and consist of two resistors (corresponding to the impedance of the vessel, at the end of which the boundary conditions are set and the friction forces in microcirculatory bed) and one capacitor (describing the elastic properties of arterioles). The numerical simulations were performed: the propagation of blood in a network of three vessels was considered, the boundary conditions for the blood flow were set at the entrance of the network, RCR boundary conditions were stated at the ends of the network. The solutions to lattice Boltzmann model are compared with the benchmark solutions (based on numerical calculations for second-order McCormack difference scheme without viscous terms), it is shown that the both approaches give very similar results.

The paper gives a detailed description of the developed methods for simulating the turbulent flow around a helicopter rotor and calculating its aerodynamic characteristics. The system of Reynolds-averaged Navier – Stokes equations for a viscous compressible gas closed by the Spalart –Allmaras turbulence model is used as the basic mathematical model. The model is formulated in a non-inertial rotating coordinate system associated with a rotor. To set the boundary conditions on the surface of the rotor, wall functions are used.

The numerical solution of the resulting system of differential equations is carried out on mixed-element unstructured grids including prismatic layers near the surface of a streamlined body.The numerical method is based on the original vertex-centered finite-volume EBR schemes. A feature of these schemes is their higher accuracy which is achieved through the use of edge-based reconstruction of variables on extended quasi-onedimensional stencils, and a moderate computational cost which allows for serial computations. The methods of Roe and Lax – Friedrichs are used as approximate Riemann solvers. The Roe method is corrected in the case of low Mach flows. When dealing with discontinuities or solutions with large gradients, a quasi-one-dimensional WENO scheme or local switching to a quasi-one-dimensional TVD-type reconstruction is used. The time integration is carried out according to the implicit three-layer second-order scheme with Newton linearization of the system of difference equations. To solve the system of linear equations, the stabilized conjugate gradient method is used.

The numerical methods are implemented as a part of the in-house code NOISEtte according to the two-level MPI–OpenMP parallel model, which allows high-performance computations on meshes consisting of hundreds of millions of nodes, while involving hundreds of thousands of CPU cores of modern supercomputers.

Based on the results of numerical simulation, the aerodynamic characteristics of the helicopter rotor are calculated, namely, trust, torque and their dimensionless coefficients.

Validation of the developed technique is carried out by simulating the turbulent flow around the Caradonna – Tung two-blade rotor and the KNRTU-KAI four-blade model rotor in hover mode mode, tail rotor in duct, and rigid main rotor in oblique flow. The numerical results are compared with the available experimental data.

Numerical simulation of hull flow, marine propellers and other basic problems of ship hydrodynamics using Cartesian adaptive locally-refined grids is advantageous with respect to numerical setup and makes an express analysis very convenient. However, when more accurate viscous phenomena are needed, they condition some problems including a sharp increase of cell number due to high levels of main grid adaptation needed to resolve boundary layers and time step decrease in simulations with a free surface due to decrease of transit time in adapted cells. To avoid those disadvantages, additional boundary layer grids are suggested for resolution of boundary layers. The boundary layer grids are one-dimensional adaptations of main grid layers nearest to a wall, which are built along a normal direction. The boundary layer grids are additional (or chimerical), their volumes are not subtracted from main grid volumes. Governing equations of flow are integrated in both grids simultaneously, and the solutions are merged according to a special algorithm. In simulations of ship hull flow boundary layer grids are able to provide sufficient conditions for low-Reynolds turbulence models and significantly improve flow structure in continues boundary layers along smooth surfaces. When there are flow separations or other complex phenomena on a hull surface, it can be subdivided into regions, and the boundary layer grids should be applied to the regions with simple flow only. This still provides a drastic decrease of computational efforts. In simulations of marine propellers, the boundary layer grids are able to provide refuse of wall functions on blade surfaces, what leads to significantly more accurate hydrodynamic forces. Altering number and configuration of boundary grid layers, it is possible to vary a boundary layer resolution without change of a main grid. This makes the boundary layer grids a suitable tool to investigate scale effects in both problems considered.

Hemostatic system serves the organism for urgent repairs of damaged blood vessel walls. Its main components – platelets, the smallest blood cells, – are constantly contained in blood and quickly adhere to the site of injury. Platelet migration across blood flow and their hit with the wall are governed by blood flow conditions and, in particular, by the physical presence of other blood cells – erythrocytes. In this review we consider the main regularities of this influence, available mathematical models of platelet migration across blood flow and adhesion based on "convection-diffusion" PDEs, and discuss recent advances in this field. Understanding of the mechanisms of these processes is necessary for building of adequate mathematical models of hemostatic system functioning in blood flow in normal and pathological conditions.