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The refraction of an oblique shock wave on a tangential discontinuity dividing two gas flows with different properties is considered. It is shown that its partial reflection occurs with the exception of the geometrical diffraction of an oblique shock. Another oblique shock, expansion wave or weak discontinuity that coincides with the Mach line can act as a reflected disturbance. This study focuses on the relationships that define the type of reflected discontinuity and its parameters. The domains of shock wave configurations with various types of reflected discontinuities, including characteristic refraction and refraction patterns with a reflected shock and a reflected rarefaction wave, are analyzed. The domains of existence of various shock wave structures with two types of reflected disturbance, and the boundaries between them, are defined. The domains of parameters with one or two solutions exist for the characteristic refraction. Each domain is mapped by the type of refraction with regard to the Mach number, the ratio of the specific heat capacities of the two flows and the intensity of a refracted oblique shock wave. The conditions of the regular refraction and the Mach refraction are formulated, and the boundaries between the two refraction types are defined for various types of gases. Refraction phenomena in various engineering problems (hydrocarbon gaseous fuel and its combustion products, diatomic gas, fuel mixture of oxygen and hydrogen, etc.) are discussed. The result can be applied to the modeling of the shock wave processes that occur in supersonic intakes and in rotating and stationary detonation engines. The solutions derived can be used by other researchers to check the quality of numerical methods and the correctness of experimental results.
Pavel Bulat; Anzhelika Melnikova; Vladimir Upyrev; Konstantin Volkov. Refraction of Oblique Shock Wave on a Tangential Discontinuity. Fluids 2021, 6, 301 .
AMA StylePavel Bulat, Anzhelika Melnikova, Vladimir Upyrev, Konstantin Volkov. Refraction of Oblique Shock Wave on a Tangential Discontinuity. Fluids. 2021; 6 (9):301.
Chicago/Turabian StylePavel Bulat; Anzhelika Melnikova; Vladimir Upyrev; Konstantin Volkov. 2021. "Refraction of Oblique Shock Wave on a Tangential Discontinuity." Fluids 6, no. 9: 301.
A numerical simulation of the gas-dynamic processes in the thrust vectorable nozzle of the solid rocket motor is considered. Construction of a geometric model and a generation of computational mesh, and reconstruction of model and mesh at each time step are discussed. Calculations of the flowfield of combustion products in the pre-nozzle chamber and nozzle block are carried out for various angles of nozzle rotation. The distributions of the gas dynamic quantities in the pre-nozzle volume corresponding to the outflow of the combustion products from the cylindrical channel and star-shaped channel are compared, as well as the solutions of the problem obtained with quasi-stationary and unsteady formulations. The effects of the channel shape on the distribution of flow quantities and formation of a vortical flow structure in the nozzle block are discussed.
Sergey Denisikhin; Vladislav Emelyanov; Konstantin Volkov. Fluid Dynamics of Thrust Vectorable Submerged Nozzle. Fluids 2021, 6, 278 .
AMA StyleSergey Denisikhin, Vladislav Emelyanov, Konstantin Volkov. Fluid Dynamics of Thrust Vectorable Submerged Nozzle. Fluids. 2021; 6 (8):278.
Chicago/Turabian StyleSergey Denisikhin; Vladislav Emelyanov; Konstantin Volkov. 2021. "Fluid Dynamics of Thrust Vectorable Submerged Nozzle." Fluids 6, no. 8: 278.
Power generation from wind energy is almost entirely performed in rural locations or at sea, and very little attention has been given to the use of wind turbines in urban locations. Since the re-emergence of wind turbines, the majority of their applications are in large commercial wind farms in rural areas or out at sea, and there is an increasing focus on the use of wind turbines within an urban environment possibly using existing structures, such as bridges and viaducts. There are very few existing buildings which have been designed from the ground-up to include wind turbines in the structure. In order to estimate the wind resources and the performance of a turbine at a particular site, a CFD model is designed and CFD calculations are performed. In order to simplify the modelling of a wind turbine actuator, disc theory is applied. Actuator disc theory is used, as it allows the aerodynamic behaviour of a wind turbine to be analyzed by just considering the energy extraction process without a specific wind turbine design. The power output of wind turbines installed beneath an already existing civil infrastructure is determined and analyzed.
Samuel Handsaker; Iheanyichukwu Ogbonna; Konstantin Volkov. CFD Prediction of Performance of Wind Turbines Integrated in the Existing Civil Infrastructure. Sustainability 2021, 13, 8514 .
AMA StyleSamuel Handsaker, Iheanyichukwu Ogbonna, Konstantin Volkov. CFD Prediction of Performance of Wind Turbines Integrated in the Existing Civil Infrastructure. Sustainability. 2021; 13 (15):8514.
Chicago/Turabian StyleSamuel Handsaker; Iheanyichukwu Ogbonna; Konstantin Volkov. 2021. "CFD Prediction of Performance of Wind Turbines Integrated in the Existing Civil Infrastructure." Sustainability 13, no. 15: 8514.
The optimal design of the thrust vector control system of solid rocket motors (SRMs) is discussed. The injection of a supersonic underexpanded gas jet into the diverging part of the rocket engine nozzle is considered, and multiparameter optimization of the geometric shape of the injection nozzle and the parameters of jet injection into a supersonic flow is developed. The turbulent flow of viscous compressible gas in the main nozzle and injection system is simulated with the Reynolds-averaged Navier–Stokes (RANS) equations and shear stress transport (SST) turbulence model. An optimization procedure with the automatic generation of a block-structured mesh and conjugate gradient method is applied to find the optimal parameters of the problem of interest. Optimization parameters include the pressure ratio of the injected jet, the angle of inclination of the injection nozzle to the axis of the main nozzle, the distance of the injection nozzle from the throat of the main nozzle and the shape of the outlet section of the injection nozzle. The location of injection nozzle varies from 0.1 to 0.9 with respect to the length of the supersonic part of the nozzle; the angle of injection varies from 30 to 160 degrees; and the shape of the outlet section of the injection nozzle is an ellipse with an aspect ratio that varies from 0.1 to 1. The computed fluid flow in the combustion chamber is compared with experimental and computational results. The dependence of the thrust as a function of the injection parameters is obtained, and conclusions are made about the effects of the input parameters of the problem on the thrust coefficient.
Vladislav Emelyanov; Mikhail Yakovchuk; Konstantin Volkov. Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle. Energies 2021, 14, 4359 .
AMA StyleVladislav Emelyanov, Mikhail Yakovchuk, Konstantin Volkov. Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle. Energies. 2021; 14 (14):4359.
Chicago/Turabian StyleVladislav Emelyanov; Mikhail Yakovchuk; Konstantin Volkov. 2021. "Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle." Energies 14, no. 14: 4359.
The design of wind turbines requires a deep insight into their complex aerodynamics, such as dynamic stall of a single airfoil and flow vortices. The calculation of the aerodynamic forces on the wind turbine blade at different angles of attack (AOAs) is a fundamental task in the design of the blades. The accurate and efficient calculation of aerodynamic forces (lift and drag) and the prediction of stall of an airfoil are challenging tasks. Computational fluid dynamics (CFD) is able to provide a better understanding of complex flows induced by the rotation of wind turbine blades. A numerical simulation is carried out to determine the aerodynamic characteristics of a single airfoil in a wide range of conditions. Reynolds-averaged Navier–Stokes (RANS) equations and large-eddy simulation (LES) results of flow over a single NACA0012 airfoil are presented in a wide range of AOAs from low lift through stall. Due to the symmetrical nature of airfoils, and also to reduce computational cost, the RANS simulation is performed in the 2D domain. However, the 3D domain is used for the LES calculations with periodical boundary conditions in the spanwise direction. The results obtained are verified and validated against experimental and computational data from previous works. The comparisons of LES and RANS results demonstrate that the RANS model considerably overpredicts the lift and drag of the airfoil at post-stall AOAs because the RANS model is not able to reproduce vorticity diffusion and the formation of the vortex. LES calculations offer good agreement with the experimental measurements.
Samuel Mitchell; Iheanyichukwu Ogbonna; Konstantin Volkov. Aerodynamic Characteristics of a Single Airfoil for Vertical Axis Wind Turbine Blades and Performance Prediction of Wind Turbines. Fluids 2021, 6, 257 .
AMA StyleSamuel Mitchell, Iheanyichukwu Ogbonna, Konstantin Volkov. Aerodynamic Characteristics of a Single Airfoil for Vertical Axis Wind Turbine Blades and Performance Prediction of Wind Turbines. Fluids. 2021; 6 (7):257.
Chicago/Turabian StyleSamuel Mitchell; Iheanyichukwu Ogbonna; Konstantin Volkov. 2021. "Aerodynamic Characteristics of a Single Airfoil for Vertical Axis Wind Turbine Blades and Performance Prediction of Wind Turbines." Fluids 6, no. 7: 257.
A lift-driven vertical axis wind turbine (VAWT) generates peak power when it is rotating at high tip-speed ratios (TSR), at which time the blades encounter angles of attack (AOA) over a small range from zero to 30 degrees. However, its ability to self-start is dependent upon its performance at low TSRs, at which time the blades encounter a range of AOAs from zero to 180 degrees. A novel vented aerofoil is presented with the intention of improving the performance of a lift-driven VAWT at low TSRs without hampering the performance of the wind turbine at high TSRs. Computational fluid dynamics (CFD) simulation is used to predict the aerodynamic characteristics of a new vented aerofoil based on the well documented NACA0012 profile. Simulations are performed using the SST turbulence model. The results obtained show a reduction in the coefficient of tangential force (the force that generates torque on the wind turbine) at low AOAs (less than 90 degrees) of no more than 30%, while at high AOAs (more than 90 degrees) an improvement in the tangential force of over 100% is observed. Using a simple momentum based performance prediction model, these results suggest that this would lead to an increase in torque generation by a theoretical three-bladed VAWT of up to 20% at low TSRs and a minor reduction in coefficient of performance of up to 9% at TSR of 2 and closer to 1% at higher TSRs.
Samuel Mitchell; Iheanyichukwu Ogbonna; Konstantin Volkov. Improvement of Self-Starting Capabilities of Vertical Axis Wind Turbines with New Design of Turbine Blades. Sustainability 2021, 13, 3854 .
AMA StyleSamuel Mitchell, Iheanyichukwu Ogbonna, Konstantin Volkov. Improvement of Self-Starting Capabilities of Vertical Axis Wind Turbines with New Design of Turbine Blades. Sustainability. 2021; 13 (7):3854.
Chicago/Turabian StyleSamuel Mitchell; Iheanyichukwu Ogbonna; Konstantin Volkov. 2021. "Improvement of Self-Starting Capabilities of Vertical Axis Wind Turbines with New Design of Turbine Blades." Sustainability 13, no. 7: 3854.
A sub-critical microwave discharge is used to achieve a stable ignition and combustion of lean air-fuel mixtures in a long tube. The microwave discharge is burnt at the presence of initiator with the quasi-optical microwave beam. The resonance way of initiation of a microwave discharge is more effective compared to traditional plasma-assisted ways of ignition and stabilization of combustion. The experimental observations show that ignition and combustion of a lean air and propane mixture in a long tube is achieved at low ignition limit with fuel/air ratio lower than 0.55. The results obtained are useful for design of new and improvement of the existing plasma-assisted technologies in aviation industry.
P V Bulat; I I Esakov; L P Grachev; K N Volkov. Combustion of lean fuel mixtures with subcritical streamer microwave discharge. IOP Conference Series: Materials Science and Engineering 2021, 1047, 012052 .
AMA StyleP V Bulat, I I Esakov, L P Grachev, K N Volkov. Combustion of lean fuel mixtures with subcritical streamer microwave discharge. IOP Conference Series: Materials Science and Engineering. 2021; 1047 (1):012052.
Chicago/Turabian StyleP V Bulat; I I Esakov; L P Grachev; K N Volkov. 2021. "Combustion of lean fuel mixtures with subcritical streamer microwave discharge." IOP Conference Series: Materials Science and Engineering 1047, no. 1: 012052.
Aluminized composite propellant used in solid rocket motors contain a lot of aluminium particles because high combustion energy is generated and propulsion efficiency increases by burning aluminium particles. The combustion of aluminum occurs in a significant portion of the combustion chamber and produces aluminum oxide smokes and residues that are carried into the flowfield. Agglomerates have non-spherical shape, and consist of aluminium droplet and oxide particle (oxide cap) attached to the droplet. Unlike the liquid droplet ignition, the solid oxide film blocks the liquid aluminum from the penetration of the oxidizer hence prevents the particle from its ignition. Development of robust models of aluminum particle dynamics is essential in the design of advanced propulsion systems. The mathematical model of two-phase flow around a single aluminum droplet with oxide cap is developed. The model solves the continuity, momentum, energy and species continuity equations simultaneously to obtain the species and temperature profiles and the burning time of droplet. The results of numerical simulations are compared with predictions from semi-empirical correlations and computational data.
V.N. Emelyanov; I.V. Teterina; K.N. Volkov. Dynamics and combustion of single aluminium agglomerate in solid propellant environment. Acta Astronautica 2020, 176, 682 -694.
AMA StyleV.N. Emelyanov, I.V. Teterina, K.N. Volkov. Dynamics and combustion of single aluminium agglomerate in solid propellant environment. Acta Astronautica. 2020; 176 ():682-694.
Chicago/Turabian StyleV.N. Emelyanov; I.V. Teterina; K.N. Volkov. 2020. "Dynamics and combustion of single aluminium agglomerate in solid propellant environment." Acta Astronautica 176, no. : 682-694.
When gas flows at a high speed in a channel with a variable cross sectional area and high-intensity energy supply, it experiences complicated physical and chemical processes producing high-temperature gas effects. High-temperature gas effects are a key issue related to design and optimization of nozzles of plasmatron of alternating current. The finite volume method is applied to solve unsteady compressible Euler equations with high-temperature gas effects. Solutions of some benchmark test cases are reported, and comparison between computational results of chemically equilibrium and perfect air flowfields is performed. The results of numerical simulation of one-dimensional and two-dimensional under- and over-expanded nozzle flows with a moving region of energy supply are presented. Output nozzle parameters are calculated as functions of a number and time of burning of plasmatron arcs. The results obtained show a qualitative pattern of gas dynamics and thermal processes in the nozzle with unsteady energy supply demonstrating the displacement of the nozzle shock wave towards the nozzle outlet in the over-expanded nozzle flow in comparison to perfect gas flow.
N.A. Brykov; V.N. Emelyanov; A.G. Karpenko; K.N. Volkov. Flows of real gas in nozzles with unsteady local energy supply. Computers & Mathematics with Applications 2019, 81, 702 -724.
AMA StyleN.A. Brykov, V.N. Emelyanov, A.G. Karpenko, K.N. Volkov. Flows of real gas in nozzles with unsteady local energy supply. Computers & Mathematics with Applications. 2019; 81 ():702-724.
Chicago/Turabian StyleN.A. Brykov; V.N. Emelyanov; A.G. Karpenko; K.N. Volkov. 2019. "Flows of real gas in nozzles with unsteady local energy supply." Computers & Mathematics with Applications 81, no. : 702-724.
The mathematical models and computational tools for design, analysis and predictions of supersonic jet and nozzle flows in the aerodynamic windows of high-power gas lasers are considered. The steady-state Euler equations describing strong shock waves, contact discontinuities, rarefaction waves and their interactions are solved with the finite-volume solver and space-marching method. The results of numerical simulation of steady-state supersonic flows of inviscid compressible gas in nozzles and under- and over-expanded jets are obtained and analyzed for different pressure ratios in the laser cavity and ambient atmosphere. The flowfields corresponding to the uniform velocity profile and free-vortex velocity profile in the outlet nozzle boundary are compared. Nozzle profiling tools are developed on the basis of numerical solution of a sequence of direct problems. The aerodynamic performance of the window is evaluated in terms of the simulated laser cavity pressure and plenum pressure of the free-vortex supply nozzle. The pressure support characteristic for the aerodynamic window is established by determining the ambient to cavity pressure ratio over a range of aerodynamic window supply pressures.
V.N. Emelyanov; A.V. Pustovalov; K.N. Volkov. Supersonic jet and nozzle flows in uniform-flow and free-vortex aerodynamic windows of gas lasers. Acta Astronautica 2019, 163, 232 -243.
AMA StyleV.N. Emelyanov, A.V. Pustovalov, K.N. Volkov. Supersonic jet and nozzle flows in uniform-flow and free-vortex aerodynamic windows of gas lasers. Acta Astronautica. 2019; 163 ():232-243.
Chicago/Turabian StyleV.N. Emelyanov; A.V. Pustovalov; K.N. Volkov. 2019. "Supersonic jet and nozzle flows in uniform-flow and free-vortex aerodynamic windows of gas lasers." Acta Astronautica 163, no. : 232-243.
M.P. Bulat; P.V. Bulat; P.V. Denissenko; I.I. Esakov; L.P. Grachev; K.N. Volkov; I.A. Volobuev. Ignition of lean and stoichiometric air–propane mixture with a subcritical microwave streamer discharge. Acta Astronautica 2018, 150, 153 -161.
AMA StyleM.P. Bulat, P.V. Bulat, P.V. Denissenko, I.I. Esakov, L.P. Grachev, K.N. Volkov, I.A. Volobuev. Ignition of lean and stoichiometric air–propane mixture with a subcritical microwave streamer discharge. Acta Astronautica. 2018; 150 ():153-161.
Chicago/Turabian StyleM.P. Bulat; P.V. Bulat; P.V. Denissenko; I.I. Esakov; L.P. Grachev; K.N. Volkov; I.A. Volobuev. 2018. "Ignition of lean and stoichiometric air–propane mixture with a subcritical microwave streamer discharge." Acta Astronautica 150, no. : 153-161.
V.N. Emelyanov; I.V. Teterina; K.N. Volkov; M.S. Yakovchuk. Aero-optical effects in free and wall-bounded turbulent compressible flows. Acta Astronautica 2018, 150, 144 -152.
AMA StyleV.N. Emelyanov, I.V. Teterina, K.N. Volkov, M.S. Yakovchuk. Aero-optical effects in free and wall-bounded turbulent compressible flows. Acta Astronautica. 2018; 150 ():144-152.
Chicago/Turabian StyleV.N. Emelyanov; I.V. Teterina; K.N. Volkov; M.S. Yakovchuk. 2018. "Aero-optical effects in free and wall-bounded turbulent compressible flows." Acta Astronautica 150, no. : 144-152.
P.V. Bulat; O.P. Minin; K.N. Volkov. Numerical simulation of optical breakdown in a liquid droplet induced by a laser pulse. Acta Astronautica 2018, 150, 162 -171.
AMA StyleP.V. Bulat, O.P. Minin, K.N. Volkov. Numerical simulation of optical breakdown in a liquid droplet induced by a laser pulse. Acta Astronautica. 2018; 150 ():162-171.
Chicago/Turabian StyleP.V. Bulat; O.P. Minin; K.N. Volkov. 2018. "Numerical simulation of optical breakdown in a liquid droplet induced by a laser pulse." Acta Astronautica 150, no. : 162-171.
The development of computational gas dynamics (CFD) and computer technologies makes it possible to design and implement methods for computing unsteady three-dimensional viscous compressible flows in regions of complex geometry. Multigrid and preconditioning techniques allowing to speed up CFD calculations on unstructured meshes were discussed in this chapter. Flow solution was provided using cell-centered finite volume formulation of unsteady three-dimensional compressible Navier–Stokes equations on unstructured meshes. The CFD code uses an edge-based data structure to give the flexibility to run on meshes composed of a variety of cell types. The fluxes were calculated on the basis of flow variables at nodes at either end of an edge or an area associated with that edge (edge weight). The edge weights were precomputed and took into account the geometry of the cell. The nonlinear CFD solver works in an explicit time-marching fashion, based on a multistep Runge–Kutta stepping procedure and piecewise parabolic method (PPM). The governing equations were solved with MUSCL-type scheme for inviscid fluxes, and the central difference scheme of the second order for viscous fluxes. Convergence to a steady state was accelerated by the use of multigrid techniques, and by the application of block Jacobi preconditioning for high-speed flows, with a separate low Mach number preconditioning method for use with low-speed flows. The capabilities of the developed approaches were demonstrated through solving some benchmark problems on structured and unstructured meshes.
Konstantin Volkov. Multigrid and Preconditioning Techniques in CFD Applications. CFD Techniques and Thermo-Mechanics Applications 2018, 83 -149.
AMA StyleKonstantin Volkov. Multigrid and Preconditioning Techniques in CFD Applications. CFD Techniques and Thermo-Mechanics Applications. 2018; ():83-149.
Chicago/Turabian StyleKonstantin Volkov. 2018. "Multigrid and Preconditioning Techniques in CFD Applications." CFD Techniques and Thermo-Mechanics Applications , no. : 83-149.
The finite volume method is applied to solve unsteady three-dimensional compressible Navier–Stokes equations on unstructured meshes. High-temperature gas effects altering the aerodynamics of vehicles are taken into account. Possibilities of the use of graphics processor units (GPUs) for the simulation of hypersonic flows are demonstrated. Solutions of some test cases on GPUs are reported, and a comparison between computational results of equilibrium chemically reacting and perfect air flowfields is performed. Speedup of solution on GPUs with respect to the solution on central processor units (CPUs) is compared. The results obtained provide promising perspective for designing a GPU-based software framework for practical applications.
Vladislav Emelyanov; Anton Karpenko; Konstantin Volkov. Numerical simulation of air hypersonic flows with equilibrium chemical reactions. THE EIGHTH POLYAKHOV’S READING: Proceedings of the International Scientific Conference on Mechanics 2018, 1959, 050010 .
AMA StyleVladislav Emelyanov, Anton Karpenko, Konstantin Volkov. Numerical simulation of air hypersonic flows with equilibrium chemical reactions. THE EIGHTH POLYAKHOV’S READING: Proceedings of the International Scientific Conference on Mechanics. 2018; 1959 (1):050010.
Chicago/Turabian StyleVladislav Emelyanov; Anton Karpenko; Konstantin Volkov. 2018. "Numerical simulation of air hypersonic flows with equilibrium chemical reactions." THE EIGHTH POLYAKHOV’S READING: Proceedings of the International Scientific Conference on Mechanics 1959, no. 1: 050010.
Andrey Kozelkov; S.V. Lashkin; Valentin Efremov; K.N. Volkov; Yu. A. Tsibereva; N.V. Tarasova. An implicit algorithm of solving Navier–Stokes equations to simulate flows in anisotropic porous media. Computers & Fluids 2018, 160, 164 -174.
AMA StyleAndrey Kozelkov, S.V. Lashkin, Valentin Efremov, K.N. Volkov, Yu. A. Tsibereva, N.V. Tarasova. An implicit algorithm of solving Navier–Stokes equations to simulate flows in anisotropic porous media. Computers & Fluids. 2018; 160 ():164-174.
Chicago/Turabian StyleAndrey Kozelkov; S.V. Lashkin; Valentin Efremov; K.N. Volkov; Yu. A. Tsibereva; N.V. Tarasova. 2018. "An implicit algorithm of solving Navier–Stokes equations to simulate flows in anisotropic porous media." Computers & Fluids 160, no. : 164-174.
A pulse detonation engine is an unsteady propulsive device in which the combustion chamber is periodically filled with a reactive gas mixture, a detonation is initiated, the detonation wave propagates through the chamber, and the combustion products are exhausted. The high pressures and resultant momentum flux out of the chamber generate thrust. The use of laser pulse allows to create desired temporal and spatial distributions of ignition centers and to perform a homogeneous ignition within the sub-microsecond interval. In the propagation of a detonation wave in a curvilinear channel (e.g., in a toroidal channel), reflection of detonation wave from the channel walls can be regular or Mach with the formation of triple points. A rapid combustion, as shown by previous experience, takes place behind the Mach stem.
P. Bulat; K. Volkov. Simulation of Laser-Induced Detonation in Particulate Systems with Applications to Pulse Detonation Engines. 30th International Symposium on Shock Waves 1 2017, 405 -409.
AMA StyleP. Bulat, K. Volkov. Simulation of Laser-Induced Detonation in Particulate Systems with Applications to Pulse Detonation Engines. 30th International Symposium on Shock Waves 1. 2017; ():405-409.
Chicago/Turabian StyleP. Bulat; K. Volkov. 2017. "Simulation of Laser-Induced Detonation in Particulate Systems with Applications to Pulse Detonation Engines." 30th International Symposium on Shock Waves 1 , no. : 405-409.
Thrust vectoring technique can deflect the mean flow of an engine jet from the centerline in order to transfer some force to the aimed axis. The secondary injection thrust vector control is particularly attractive for thrust vectoring in large boosters (especially solid propellant rocket) where large side thrust is generated. Injection of a secondary fluid into the divergent section of the nozzle causes an asymmetrical distortion of the exhaust gas flow. In addition to providing a propulsive force to a flying vehicle or a rocket, a rocket propulsion system can also provide certain control mechanisms to change vehicle’s attitude and trajectory via thrust vector control systems. On contrary to mechanically operating thrust vector control systems, such as gimbaled nozzles and jet vanes, which require actuators to deflect mechanical parts, secondary injection does not require any moving parts and regulated by the fluid injection, which reduces axial thrust force losses while changing the direction of the vector.
V. Emelyanov; K. Volkov; M. Yakovchuck. Transverse Jet Injection into a Supersonic Nozzle Flow. 30th International Symposium on Shock Waves 1 2017, 77 -81.
AMA StyleV. Emelyanov, K. Volkov, M. Yakovchuck. Transverse Jet Injection into a Supersonic Nozzle Flow. 30th International Symposium on Shock Waves 1. 2017; ():77-81.
Chicago/Turabian StyleV. Emelyanov; K. Volkov; M. Yakovchuck. 2017. "Transverse Jet Injection into a Supersonic Nozzle Flow." 30th International Symposium on Shock Waves 1 , no. : 77-81.
K.N. Volkov; P.V. Bulat; I.A. Volobuev; V.A. Pronin. Heat transfer in a cavity with rotating disk in turbulent regime. Scientific and Technical Journal of Information Technologies, Mechanics and Optics 2017, 514 -524.
AMA StyleK.N. Volkov, P.V. Bulat, I.A. Volobuev, V.A. Pronin. Heat transfer in a cavity with rotating disk in turbulent regime. Scientific and Technical Journal of Information Technologies, Mechanics and Optics. 2017; ():514-524.
Chicago/Turabian StyleK.N. Volkov; P.V. Bulat; I.A. Volobuev; V.A. Pronin. 2017. "Heat transfer in a cavity with rotating disk in turbulent regime." Scientific and Technical Journal of Information Technologies, Mechanics and Optics , no. : 514-524.
Computational methods are widely used in prediction of complex flowfields associated with off-normal situations in aerospace engineering. Modern graphics processing units (GPU) provide architectures and new programming models that enable to harness their large processing power and to design computational fluid dynamics (CFD) simulations at both high performance and low cost. Possibilities of the use of GPUs for the simulation of external and internal flows on unstructured meshes are discussed. The finite volume method is applied to solve three-dimensional unsteady compressible Euler and Navier–Stokes equations on unstructured meshes with high resolution numerical schemes. CUDA technology is used for programming implementation of parallel computational algorithms. Solutions of some benchmark test cases on GPUs are reported, and the results computed are compared with experimental and computational data. Approaches to optimization of the CFD code related to the use of different types of memory are considered. Speedup of solution on GPUs with respect to the solution on central processor unit (CPU) is compared. Performance measurements show that numerical schemes developed achieve 20–50 speedup on GPU hardware compared to CPU reference implementation. The results obtained provide promising perspective for designing a GPU-based software framework for applications in CFD.
V.N. Emelyanov; A.G. Karpenko; A.S. Kozelkov; I.V. Teterina; K.N. Volkov; A.V. Yalozo. Analysis of impact of general-purpose graphics processor units in supersonic flow modeling. Acta Astronautica 2017, 135, 198 -207.
AMA StyleV.N. Emelyanov, A.G. Karpenko, A.S. Kozelkov, I.V. Teterina, K.N. Volkov, A.V. Yalozo. Analysis of impact of general-purpose graphics processor units in supersonic flow modeling. Acta Astronautica. 2017; 135 ():198-207.
Chicago/Turabian StyleV.N. Emelyanov; A.G. Karpenko; A.S. Kozelkov; I.V. Teterina; K.N. Volkov; A.V. Yalozo. 2017. "Analysis of impact of general-purpose graphics processor units in supersonic flow modeling." Acta Astronautica 135, no. : 198-207.