Search

A stabler ignition and combustion of the premixed air/fuel mixture remains a topic of great interest due to the high demand for effective and efficient propulsion systems in aerospace applications. Extensive experimental studies and numerical simulations have been carried out to understand and develop ignition systems using cold and non-thermal plasma in microwave streamer discharges. Use of sub-critical streamer discharge allows to ignite air/fuel mixture by an external electric field whose intensity is significantly lower than the intensity required to induce air breakdown. Ignition and combustion of air/propane mixture by microwave sub-critical streamer discharge in low- and high-speed flows is studied experimentally. Qualitative (flame structure) and quantitative (size of combustion region, temperature distributions) characteristics of the flame zone are provided for different flow speeds and equivalence fuel/air ratios, and conditions of discharge initiation with metallic microwave vibrator are studied. The streamer discharge makes it possible to create multiple ignition points providing almost instantaneous ignition of entire volume of the mixture. The results show that the sub-critical streamer discharge can potentially be used in various applications providing more rapid and efficient combustion.

Quantum capacitance CQ of an infinite graphene sheet, a graphene nanoribbon, and a chain of carbon atoms (carbyne) have been analytically estimated within the framework of simple models. A nonmonotonic dependence of CQ on the electrostatic potential is demonstrated. The data obtained are compared with the calculation results of other researchers.

In this paper, we study the intersection (interaction) between several steady shocks traveling in the same direction. The interaction between overtaking shocks may be regular or irregular. In the case of regular reflection, the intersection of overtaking shocks leads to the formation of a resulting shock, contact discontinuity, and some reflected discontinuities. The type of discontinuity depends on the parameters of incoming shocks. At the irregular reflection, a Mach shock forms between incoming overtaking shocks. Reflected discontinuities come from the points of intersection of the Mach stem with the incoming shocks. We also consider the possible types of shockwave configurations that form both at regular and irregular interactions of several overtaking shocks. The regions of existence of overtaking shock waves with different types of reflected shock and the intensity of reflected shocks are defined. The results obtained in the study can potentially be useful for designing supersonic intakes and advanced jet engines.

We have studied the effect of temperature and etching duration of the 4H-SiC (0001) surface in hydrogen on the structural perfection of graphene films grown by thermal destruction. Several technological modes have been identified that enable etching of the substrate without changing the stoichiometric composition of the surface. It has been demonstrated that pregrowth etching in hydrogen at T = 1600°C with a duration of 1 min makes it possible to obtain a more uniform and structurally perfect graphene than etching at T = 1300°C with a 30 min duration.

We have studied the structure of epitaxial graphene obtained as a result of thermal desorption of the silicon carbide surface under conditions of vacuum synthesis and in Ar medium by reflection electron diffraction. As a result of the study, a significantly more uniform buffer layer coating of the SiC surface by epitaxial graphene has been found when forming in inert medium on the surface of 4H- and 6H-SiC(0001) polytypes compared with the synthesis of graphene in high vacuum. The quality of the coating has been shown to depend on the degree of perfection of the original single crystal.

The results of experimental studies of combustion of propane–air gaseous mixture when it was ignited by a microwave discharge have been described. The mixture with different propane content fills a sealed radio-transparent tube placed along the axis of a focused linearly polarized quasi-optical microwave beam at atmospheric pressure. Multi-point ignition of the mixture is carried out near one end of the tube by a pulsed microwave discharge with a surface-developed streamer structure. The growth of gas pressure in the tube as propane burned was recorded in the experiments. The microwave pulse energy being invested in high-temperature discharge plasma has been estimated in them. The minimum percentage of propane in the mixture at which the microwave discharge ignites it has been determined in experiments. The time dependence of the pressure increase in the tube as the propane burns determines the combustion process dynamics.

There have been consistent efforts in developing more efficient combustion for propulsion systems. Ignition and combustion control using cold and non-thermal plasma in microwave discharges have become a major topic of interest. In this study, a microwave subcritical streamer discharge is used to initiate ignition and combustion of premixed air/fuel mixture in a long cylindrical tube. The streamer discharge is arising on the internal surface of the dielectric tube using a passive vibrator in a single pulse regime at atmospheric pressure and temperature. The propagation speed of the combustion front in the quartz cylindrical tube filled by the air/propane mixture is analyzed experimentally and numerically. The streamer discharge creating a multitude of ignition points provides practically instantaneous ignition of the mixture in the entire volume. The speed of streamer induced combustion front has been shown to be higher compared to that initiated by a spark. Increasing the length of streamer discharge leads to increasing the flame propagation speed. The combustion efficiency has also been shown to be higher when using the microwave streamer ignition.

The feasibility of air breakdown initiation by a quasi-optical subcritical-field microwave beam has been studied experimentally. Breakdown has been initiated by a linear electromagnetic vibrator, which was placed in a traveling electromagnetic wave (i) on the surface of a dielectric sheet that faces wavevector k of the wave, (ii) on the opposite surface of the sheet, and (iii) near the sheet. Fields induced at the ends of the vibrator have been calculated theoretically for all arrangements. Numerical estimates and experimental data have shown that when a vibrator is placed on a dielectric surface, electrical breakdown of air may be initiated in a much deeper subcritical field of the microwave beam than when it is placed in the field of a traveling microwave.

Microwave discharges initiated by an electromagnetic (EM) vibrator and ignited on the inner surface of a dielectric tube in a quasi-optical EM beam are experimentally studied. A threshold level of the microwave field that separates domains of subcritical and deeply subcritical microwave discharges is determined in experiments. Experiments show that streamer channels of the subcritical discharge propagate from the initiator along the propagation direction of the EM wave and in the opposite direction under certain conditions. Variations in the power of the microwave beam can be used to change length of the plasma region of the subcritical discharge along the wave vector of the microwave beam and control the level of the EM energy absorbed in the plasma regions of the deeply subcritical microwave discharge.

The main role in reducing the noise generation of unmanned aerial vehicles is played by aeroacoustic improvement of their power plant. To identify the acoustic field generated by the rotation of the impeller, which is used on an unmanned aerial vehicle of a quadcopter type, numerical modeling was carried out with the identification of the turbulent structure of the flow using the Large Eddy Simulation (LES). To calculate the noise, the Fox Williams-Hawkings (FW-H) integral method was applied, which makes it possible to determine the aeroacoustic characteristics in the far flow field. Using this technique, the noise level at various points was determined, a spectral analysis of the noise was carried out, and the directional pattern of acoustic radiation was plotted for various speeds of rotation of the propeller in hovering mode.

Pulse detonation engines are considered to be one of effective propulsion systems for future space missions. Significant efforts are being spent on acceleration of fuel combustion and rising is efficiency. Existing studies have mainly focused on optimizing fuel injection and mixing, repetitive initiation of detonation and integration of detonation tubes with fuel inlets. Understanding of streamer propagation mechanism is of essential importance for the studies of electrical breakdown phenomena and their related applications. In this study, a subcritical microwave streamer discharge is used to initiate ignition of air–fuel mixtures. Ignition of lean fuel mixtures by a streamer has been demonstrated at atmospheric pressure. The speed of streamer-initiated combustion has been shown to be higher compared to that initiated by a spark. The combustion efficiency has also been shown to be higher when using the microwave streamer ignition.

Modelling and simulation of interaction of laser pulse with individual liquid droplets are of crucial importance in terms of development and code coupling for simulation of laser propulsion and detonation in gas-droplet systems. These applications are challenging and complex for many reasons, one among them is the disparate time and length scales that are required to resolve for an accurate physical representation of the problem. The injection of liquid droplets with low evaporation temperature causes optical breakdown on the individual droplet and leads to a drop of the minimum pulse energy of detonation in the gas-droplet mixture. The mathematical models of various stages of the optical breakdown on individual droplet and numerical methodology for computer modelling of the laser-induced breakdown are developed. Sub-models of optical breakdown on liquid droplet include droplet heating to boiling temperature, its evaporation and formation of vapor aureole around the droplet, ionization of vapor aureole and development of electron avalanche, appearance of micro-plasma spots and their expansion, propagation of shock wave inside the droplet and in the surrounding gas. The threshold intensity of optical breakdown on individual water droplet and its dependence on droplet radius, location of droplet, total energy and radius of laser pulse are studied.

The bearing capacity of hybrid segmented bearings with different groove systems is compared. The research establishes that the system with a crescent groove has the best characteristics.

The method of reflection high-energy electron diffraction (RHEED) is used for studying the structure of graphene layers formed on the surface of the Si-face of conductive and semi-insulating 6H- and 4H-SiC(0001) substrates by thermal desorption of Si atoms in high vacuum, depending on the temperature and time of sublimating Si atoms as well as depending on the method of preprocessing the substrate surface. Diffraction patterns are recorded in the $$[\bar 12\bar 10]$$ and $$[1\bar 100]$$ crystallographic directions of the substrates. It is found that in all experiments the formation of graphene layers occurs with a rotation of the graphene crystal lattice by 30° relative to the SiC lattice.

Physical details regarding base pressure low-frequency oscillations between rocket nozzles, their excitation and maintenance, are considered. Amplitude – frequency characteristics of these oscillations, as well as sequence of their type change, are studied. A single nozzle, a two-nozzle unit and a ring nozzle imitating multi-nozzle unit, are investigated in the present study.

Two-phase systems that involve gas-particle or gas-droplet flows are widely used in aerospace and power engineering. The problems of weakening and suppression of detonation during saturation of a gas or liquid flow with the array of solid particles are considered. The tasks, associated with the formation of particles arrays, dust lifting behind a travelling shock wave, ignition of particles in high-speed and high-temperature gas flows are adjoined to safety of space flight. The mathematical models of shock wave interaction with the array of solid particles are discussed, and numerical methods are briefly described. The numerical simulations of interaction between sub- and supersonic flows and an array of particles being in motionless state at the initial time are performed. Calculations are carried out taking into account the influence that the particles cause on the flow of carrier gas. The results obtained show that inert particles significantly weaken the shock waves up to their suppression, which can be used to enhance the explosion safety of spacecrafts.

A variety of methods exists for fast and efficient combustion of air-fuel mixtures. In this study, a microwave subcritical streamer discharge is used to ignite propane-air mixtures at atmospheric pressure. The streamer is initiated at the inner surface of a dielectric tube with the help of a passive half-wave vibrator. By creating a network of ignition lines, the streamer discharge forms the network of burning channels with large total surface area. This leads to the apparent speed of combustion propagation along the cylinder in excess of 100 m/s, which is more than 200 times the laminar flame propagation speed. The axial propagation of the combustion front in a cylindrical tube filled with the air/propane mixture is investigated by high speed video recording in visible light. A simple model is presented to explain observed results.

Objectives: This paper considers the concept of shock wave compressor in which the compression occurs not in the impeller machine, but in the optimal system of triple shock waves configurations. Methods/Analysis: A review of the works being conducted in the world in this field is provided. The basics of the gas-dynamic discontinuities interference theory are given; the development sequence of the theory of optimal (extreme) shock-wave structures is shown. Findings: The task of designing a new gas compression device - the shock-wave compressor is considered. Differences from other similar devices are discussed. The model air intake tract for the wave compressor is designed. The calculations of the model wave machine are provided. Comparison with multistage axial compressor shows that starting with a compression ratio of 25, the degree of full throating pressure restoration, provided by a shock wave compressor is not smaller than that of an impeller machine. Although, the size and weight of the shock wave compressor is much lower. Novelty/Improvement: Relevant is the task of reducing the size and decreasing the number of stages in the high-pressure compressors of refrigerators and other turbomachinery. Our results allow us to offer the concept of the compressor in which the number of stages is significantly reduced through the use of a gas compression in optimal shock-wave structures. The potential advantage in comparison to the traditional axial compressors is demonstrated.

Subject of Research. A mathematical model of optical breakdown in the dielectric liquid droplets when exposed to pulsed laser radiation was developed. The process is considered in several stages: heating, evaporation of the particle, forming a steam halo, ionization of the steam halo. Numerical study was carried out on the basis of the mathematical model to determine the threshold characteristics of the laser pulse. Main Results.Distributions of pressure, density and temperature of the particle steam halo were obtained by means of a calculation. The temperature field around the liquid droplet was determined. It has been found that at high energies in the gas bubble, the conditions are provided for thermal gas ionization and start of the electron avalanche, leading to plasma formation. Due to the volumetric heat generation, the droplet is overheated and is in a metastable state. The plasma cloud is almost opaque to radiation that causes an abrupt increase of temperature. As a result, an explosion occurs inside the droplet with the formation of a shock wave that is propagating outward. Practical Relevance.The results can be used to assess the performance of high-power laser scanning (LIDAR) under the presence of liquid droplets in the atmosphere and other suspensions. Lasers can be used in fire and explosion aerospace systems. Obtained findings can be applied also in the systems of laser ignition and detonation initiation.

Subject of Research.The paper deals with the problem of developing low emission combustors operating on natural gas or LPG, to reduce emissions of nitrogen oxides NOx. The possibility of burning very lean fuel mixtures is studied. To initiate the ignition and combustion stabilization the discharge generated by the quasi-optical microwave is used. Main Results. Initiating ignition by streamer microwave discharge increases the rate of combustion and combustion efficiency about four times as compared with the conventional spark ignition. Streamer discharge ignition by very lean fuel-air mixture is demonstrated with the factor of oxiding agent excess greater than the limit of explosive range under normal conditions. According to indirect indicators, ignition by microwave discharge created by quasi-optical radiation is of non-thermal nature. Microwave discharge excites oxygen atoms, and intense ultra-violet radiation is generated as a result that causes formation of cold nonequilibrium plasma with avalanche growth of free electrons. Streamer discharge propagates at a speed of 5 km /s, so the initiation of the ignition occurs immediately throughout. The temperature of the fuel mixture at the point of ignition initiation does not exceed 400 К.There is no area with a temperature sufficient to initiate thermal Zeldovich mechanism of emission of nitrogen oxides. Combustion rate is high. As a result the Fenimore mechanism of "fast nitrogen oxides" has no chance to be progressing, and NOx emissions in appreciable quantities are excluded. Energy costs are comparable with spark ignition.Practical Relevance. The studied technology is designed for low emission internal combustion engines, power gas turbines, gas compressor units, fueled by natural gas.

Oblique shock waves can be reflected from hard walls, the axis, or the plane of symmetry, as well as from other counterpropagating shock waves with the formation of regular and Mach shock wave configurations. The specific form of shock wave structures is determined by the parameters of the problem: Mach number and intensity of incident shock waves. On the plane of parameters, there exists an ambiguity area in which laws of conservation admit both the regular and Mach reflection of shock waves. The boundaries of this region have been determined.

Flows and heat transfer in channels containing both fluid and porous regions play an important role in various engineering applications. A better understanding of fundamental mechanisms in the fluid flows in porous regions are required in order to design and optimise gas bearings, air filters, and thermal insulation in the specific applications. Darcy-Brinkman-Forchheimer model is used to describe the flow inside the porous domain. The finite volume method is applied to solve these equations in a porous and open domain. The capabilities of the mathematical model and computational algorithm are demonstrated using test cases from various areas of practical applications. The effect of various physical quantities on velocity and pressure distributions is studied. The results of the numerical simulation of flows in porous domains are presented. The results obtained are in a good agreement with the experimental and numerical data available in the literature.

The high pressures and resultant momentum flux out of the chamber generate thrust. The ignition system of PDE has always posed problems in commercial applications. Microwave and laser-induced detonation in the mixture ofhydrogen with flake aluminum particles is simulated based on Eulerian approach. Minimum pulse energy of detonation is calculated for different parameters of laser pulse, mass fractions of particles, and compositions of gas mixture. The threshold intensity of optical breakdown on individual metal particle, and its dependence on contributing factors (particle radius, location of particle, total energy and time of laser pulse, radius of laser spot) are studied.

Numerical simulation of the shock wave–laminar boundary layer interaction is carried out on the basis of the model problem at different Reynolds numbers. The use of WENO schemes of high order of accuracy is demonstrated. The calculated shock-wave structure of the fl ow is compared with the data available in the literature and with the data obtained from TVD schemes. Criteria of accuracy of numerical calculations that are related to the position of shock-wave structures, and also the time of solution of the problem with various difference schemes, are discussed. Recommendations on practical use of difference schemes of high order of accuracy are given.

The goal of this study is to study the conditions of dynamic compatibility on gas-dynamic discontinuities written in the form of a generalized adiabat. We have considered the basic concepts of the gas-dynamic discontinuity theory, the ratios permitting to calculate pressure shocks. Recommendations for rational problem definition and methods of solution of the typical computational problems are given. The dependences for calculation of parameters behind the shock according to the known parameters of a stream and the shock intensity recorded for the first time with the help of a generalized adiabatic line are considered. Substituting in these relations equations of adiabatic line of Laplace-Poisson, Rankine-Hugoniot and Chapman-Jouget, you can calculate the parameters behind, accordingly: simple waves, shockwaves and detonation waves. There are given in friendly graphic form the dependence on the Mach number of incoming flow and gas adiabatic index of the most relevant parameters of shocks: maximum intensity, stream deviation angle on the shock, critical angle of the stream deviation, shock angle according to the critical angle of a the stream deviation. The work can be recommended to the experts, engineers and scientists working in the field of aerospace engineering, metallurgy and metal hardening, for usage of control technologies for hypersonic currents containing gas-dynamic discontinuity.

Regular and Mach (irregular) reflection of an oblique shock wave from the wall is considered. Criteria for the transition from regular to irregular reflection are described: von Neumann criterion and the criterion for fixed Mach configuration. Specific incident shock wave intensities corresponding to the two criteria for the transition from regular to irregular reflection were plotted. The area of ambiguity solutions was demonstrated in which both regular and Mach reflection is not prohibited by the conditions of dynamic compatibility. Areas in which the transition from one type of reflection to another is possible only by a shock wave were described, as well as areas of a possible smooth transition. Dependence of the magnitude of this abrupt change in reflected discontinuity intensity from the intensity of the incident shock wave was plotted. Intensity dependences of the reflected discontinuity from the intensity of the shock wave incident on the wall for all types of reflections were shown.

The Riemann problem of one-dimensional arbitrary discontinuity breakdown for parameters of unsteady gas flow is considered as applied to the design of Godunov-type numerical methods. The problem is solved in exact and approximate statements (Osher-Solomon difference scheme used in shock capturing numerical methods): the intensities (the ratio of static pressures) and flow velocities on the sides of the resulting breakdowns and waves are determined, and then the other parameters are calculated in all regions of the flow. Comparison of calculation results for model flows by exact and approximate solutions is performed. The concept of velocity function is introduced. The dependence of the velocity function on the breakdown intensity is investigated. A special intensity at which isentropic wave creates the same flow rate as the shock wave is discovered. In the vicinity of this singular intensity approximate methods provide the highest accuracy. The domain of applicability for the approximate Osher-Solomon solution is defined by performing test calculations. The results are presented in a form suitable for usage in the numerical methods. The results obtained can be used in the high-resolution numerical methods.

We have considered the modern theory of breakdown of an arbitrary gas-dynamic discontinuity for the space-time dimension equal to two. The regions of solutions existence for a one-dimensional non-stationary case and a two-dimensional stationary case have been compared. The Riemann problem of breakdown of an arbitrary discontinuity of parameters of two flat flows angle collision is considered. The problem is solved in accurate setting. The problem parameter areas where outgoing waves appear as two jumps are specified. Two depression waves solution are not covered. The special Mach numbers of interacting flows dividing the parameter plane into areas with different outgoing discontinuities are given.

The purpose of research-the study of the flow in the center of the centered isentropic compression waves. Gas-dynamic discontinuities cover shocks, shockwaves, interfaces and sliding surfaces and also the center of the centered compression wave one-dimensional and two-dimensional. For a long time there has been no analysis of the shockwave structures arising in the center of compression waves. At the same time, the problem of development of supersonic and hypersonic air inlets demands to consider the process of the stream isentropic compression. This problem is connected (three-dimensional case) to the problem of arising inside the streams of hinged shocks as opposite to the usual discontinuities not resulted by interaction of supersonic streams, waves and discontinuities, but like from nowhere. This study sets the problem for study in the terms of the developed theory of the interference of gas-dynamic discontinuities of the area of existing solutions for the structures of possible types. We have obtained the relations describing the parameters in the center of the compression wave. We have considered the neutral polar of neither compression meeting the case when in the center of the compression wave there neither shocks nor depression waves. The analysis of properties of the centered compression wave adds to the theory of stationary gas- dynamic discontinuities. We have specified the borders of the shock structure existence area optimal for development of supersonic diffusers.

The aim of the study is to give a common classification of gasdynamic discontinuities, shock-wave structures and shock-wave processes. We have considered the classification of gas-dynamic discontinuities, shock- wave processes, shock-wave structures, discontinuity interaction problems. We have considered different classification criteria: thermodynamic, cinematic, transiency, discontinuity direction, arriving and outgoing discontinuities. A comprehensive list of discontinuity interference problems is given, as well as classification of possible transformations and wave front reorganization up to the case of the problem two-dimensional transient definition.

The direct problem of researching the load capacity of segment gas-static bearing is being discussed. In calculation the movement of the shaft in the bearing is considered slow comparing than the rotational velocity. Vibrations and the influence of non-stationarity are neglected. The given geometry of the bearing and the pressure of lubrication supply in the gap between the bearing and the shaft are considered initial data. The result of the calculation is the value of the resultant pressure force, applied to the bearing segments. Summing the forces the value of the static load capacity can be found. For segments that may spontaneously rotate about the joint axis, described a method of calculating the rotation angle, at which the main moment of pressure forces applied to the segment is equal to zero and the segment’s position is stable.

The purpose of the study is to determine the conditions of Mach disk (direct shock wave) in a supersonic nonisobaric jet. Brief details on shock waves triple configurations, Mach reflection of a shock wave from a rigid wall and the axis of symmetry are given. Various known semi-empirical model of calculating the Mach disc diameter in a supersonic jet and its removal from the nozzle are discussed. It is shown that the Mach disk in the jet is corresponded by the so-called stationary Mach shock waves triple configuration, in which the intensity of the main shock (Mach disk) is the maximum possible for a given Mach number. The theoretical and calculative-experimental validation of the Mach disk formation model in a supersonic non-isobaric jet is provided. The results of calculation are in satisfactory match with experiment.

Objectives: This paper considers the concept of shock wave compressor in which the compression occurs not in the impeller machine, but in the optimal system of triple shock waves configurations. Methods/Analysis: A review of the works being conducted in the world in this field is provided. The basics of the gas-dynamic discontinuities interference theory are given; the development sequence of the theory of optimal (extreme) shock-wave structures is shown. Findings: The task of designing a new gas compression device - the shock-wave compressor is considered. Differences from other similar devices are discussed. The model air intake tract for the wave compressor is designed. The calculations of the model wave machine are provided. Comparison with multistage axial compressor shows that starting with a compression ratio of 25, the degree of full throating pressure restoration, provided by a shock wave compressor is not smaller than that of an impeller machine. Although, the size and weight of the shock wave compressor is much lower. Novelty/Improvement: Relevant is the task of reducing the size and decreasing the number of stages in the high-pressure compressors of refrigerators and other turbomachinery. Our results allow us to offer the concept of the compressor in which the number of stages is significantly reduced through the use of a gas compression in optimal shock-wave structures. The potential advantage in comparison to the traditional axial compressors is demonstrated.

Background/Objectives: This article discusses the problem of refraction of the shock wave with finite amplitude at contact discontinuity between two ideal gases is non-linear, and can be solved numerically for both stationary two-dimensional and transient one-dimensional cases. Methods/Statistical Analysis: Here considered the problem of interaction of one dimensional shock wave (weak and strong) with the contact surface dividing two different gases with different chemical composition and temperature. The interface surface is considered parallel to the shock wave surface. Findings: The sound speed maximal increase in the layer after the contact discontinuity by means of the gas selection with minimal molar mass and its heating seems to be the most satisfying technical solution for the shock wave suppression. Applications/Improvements: This work can be used for both solution of the problem of the intense explosion shock wave attenuation, and the problem of optimal organisation of detonation combustion, where the wave attenuation at the interface should be minimal.

Supersonic flows of gas in the vicinity of the bottom region known as flows with sudden expansion have been considered. On the basis of extensive experimental studies, authors have proposed a complete classification of flow regimes: stationary, oscillating, and transient. Hysteresis of the regimes change at total gas pressure increasing and decreasing in front of the nozzle has been found. Typical shock-wave configurations emerging at the jet flowing in a channel at different modes have been determined. The type of shock-wave structure and the nature of interaction of the mixing layer of a jet with the wall or reverse flow flowing into the channel from ambient medium determine the appropriate mode. Combination of physical and numerical experiment with bottom pressure calculation according to the developed semi-empirical model have revealed new flow regimes that were not studied earlier.

For gas-lubricated bearings the form of a lubricating clearance in many respects determines the carrying capacity value of the bearing. Furthermore, the parameters defining this form have, for the most part, the optimal values. Today, the most typical for computation of a gas base layer is use of software with solvers which contain equations of the gas lubrication theory based on the Reynolds equation. However, the total computation of the system of gas feed into the gas-static bearing box in such setting meets methodical complications: in the gas feed system turbulent flows appear, and their computation is necessary to be carried out in the full Navier-Stokes equations with connection of the applicable model of turbulence, and there is a laminar flow in the lubricating film. The solution of the computation problem of the gas base layer in the Navier-Stokes full equations is considered. The method was verified with use of known self-similar solutions. Based on the tried-and-true method, parametric study of a pad with simple plain bores, a pad with a slotted nozzle and composite pads with angular clearances designed under the Rayleigh principle were carried out.