Pub Date : 2018-12-13DOI: 10.33257/PHCHGD.19.3.759
E. Kustova, A. Savelev
{"title":"Rate Coefficients of Exchange Reactions in Air and Carbon Dioxide","authors":"E. Kustova, A. Savelev","doi":"10.33257/PHCHGD.19.3.759","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.3.759","url":null,"abstract":"","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-12-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130288242","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-12-13DOI: 10.33257/PHCHGD.19.3.763
A. Zheleznyakova
The application of the composite grid concept in the framework of unstructured approach for the numerical simulation of flow around complex multistage space systems is discussed. The group of streamlined bodies of arbitrary configuration under the changes in the number of system elements and their mutual arrangement is considered. This technology is based on the application of overlapping unstructured grids, which are independently generated for each object of the system. The proposed aerodynamic model of system of arbitrarily located objects having complex configurations is based on the computational technologies for unstructured mesh generation and for the integration of the Navier – Stokes / Euler equations, which are developed in Institute for Problems in Mechanics Russian Academy of Sciences (IPMech RAS). The algorithm implementation requires minor source code modifications. The possibilities of the approach are demonstrated by the example of the numerical simulation of flow around complex multistage space transportation system Space Shuttle. The created virtual prototype of the space system arrangement unites in itself the set of volume grids, which are independently generated for individual stages based on the most realistic virtual surfaces. A mathematical description of the geometry of each system element contains all the basic details of the corresponding configuration.
{"title":"Overlapping unstructured grid technology for the numerical simulation of flow around multistage space system","authors":"A. Zheleznyakova","doi":"10.33257/PHCHGD.19.3.763","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.3.763","url":null,"abstract":"The application of the composite grid concept in the framework of unstructured approach for the numerical simulation of flow around complex multistage space systems is discussed. The group of streamlined bodies of arbitrary configuration under the changes in the number of system elements and their mutual arrangement is considered. This technology is based on the application of overlapping unstructured grids, which are independently generated for each object of the system. The proposed aerodynamic model of system of arbitrarily located objects having complex configurations is based on the computational technologies for unstructured mesh generation and for the integration of the Navier – Stokes / Euler equations, which are developed in Institute for Problems in Mechanics Russian Academy of Sciences (IPMech RAS). The algorithm implementation requires minor source code modifications. The possibilities of the approach are demonstrated by the example of the numerical simulation of flow around complex multistage space transportation system Space Shuttle. The created virtual prototype of the space system arrangement unites in itself the set of volume grids, which are independently generated for individual stages based on the most realistic virtual surfaces. A mathematical description of the geometry of each system element contains all the basic details of the corresponding configuration.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"69 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-12-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133733159","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-12-04DOI: 10.33257/PHCHGD.19.2.752
A. Dikalyuk, V. O. Gumennov
Modeling of temporal evolution of Penning gas discharge plasma in molecular hydrogen at pressure 0.8 mtorr, anode voltage 800 V and axial magnetic field 330 G is performed in the paper. Simulation is carried out using 2D/3V axisymmetric electrostatic PIC-MCC method. Distinct feature of this work is the addition of dissociative ionization process to kinetic model of Penning gas discharge in molecular hydrogen. In the paper temporal evolution of electrostatic potential, field, charged particles number densities and temperatures in gas discharge chamber are given.
{"title":"Modeling of Unsteady Processes in Penning Gas Discharge Plasma using PIC-MCC Method","authors":"A. Dikalyuk, V. O. Gumennov","doi":"10.33257/PHCHGD.19.2.752","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.2.752","url":null,"abstract":"Modeling of temporal evolution of Penning gas discharge plasma in molecular hydrogen at pressure 0.8 mtorr, anode voltage 800 V and axial magnetic field 330 G is performed in the paper. Simulation is carried out using 2D/3V axisymmetric electrostatic PIC-MCC method. Distinct feature of this work is the addition of dissociative ionization process to kinetic model of Penning gas discharge in molecular hydrogen. In the paper temporal evolution of electrostatic potential, field, charged particles number densities and temperatures in gas discharge chamber are given.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-12-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132090337","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/PHCHGD.19.2.725
P. Silvestrov, O. Bessonov, V. Yarmolyuk
This paper presents the general idea and the first implementation of the new visualization system – an integrated environment for viewing and analyzing results of aerogasdynamic computations and different spatial objects (vehicle surfaces, computational grids). This system is based on the open-source cross-platform development toolkits Qt and VTK. The paper describes basic functions of the visualization system and presents examples of its graphical capabilities for drawing spatial images and two-dimensional plots. Examples of dialogue boxes for controlling the process of visualization are also shown. The system supports main geometric and grid formats, as well as it is partially compatible with the popular commercial visualization system Tecplot (both in data formats and control procedures). The new system has the unified implementation for Windows and Linux operation systems and can be deployed on any modern personal computer.
{"title":"On the Concept of the National Visualization System for Aerogasdynamic Computations","authors":"P. Silvestrov, O. Bessonov, V. Yarmolyuk","doi":"10.33257/PHCHGD.19.2.725","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.2.725","url":null,"abstract":"This paper presents the general idea and the first implementation of the new visualization system – an integrated environment for viewing and analyzing results of aerogasdynamic computations and different spatial objects (vehicle surfaces, computational grids). This system is based on the open-source cross-platform development toolkits Qt and VTK. The paper describes basic functions of the visualization system and presents examples of its graphical capabilities for drawing spatial images and two-dimensional plots. Examples of dialogue boxes for controlling the process of visualization are also shown. The system supports main geometric and grid formats, as well as it is partially compatible with the popular commercial visualization system Tecplot (both in data formats and control procedures). The new system has the unified implementation for Windows and Linux operation systems and can be deployed on any modern personal computer.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134335917","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/PHCHGD.19.2.746
B. Zhestkov, A. Kireev, A. Zaytsev, Sergey V. Chertnov, V. L. Yumashev
Numerical simulation of high enthalpy flow in the nozzle of wind tunnel VAT-104 is carried out using a detailed model of nonequilibrium physical and chemical processes. An implicit staggered-grid scheme of the second order of accuracy is used to approximate the governing equations. The goals of this modeling are: (1) to test a numerical approach to simulate high temperature nonequilibrium flows, (2) to determine the role of processes important for energy exchange at the nozzle flow conditions, (3) to get numerical values of species mass fractions and molecule vibration temperatures along the nozzle and at the entry to the test part. The illustrations below show the profile of VAT-104 nozzle, the difference scheme stencils, the N and N 2 mass fraction profiles and vibration temperatures profiles along the nozzle.
{"title":"Numerical Simulation of Non-equilibrium Flow in the Nozzle of VAT-104 Wind Tunnel","authors":"B. Zhestkov, A. Kireev, A. Zaytsev, Sergey V. Chertnov, V. L. Yumashev","doi":"10.33257/PHCHGD.19.2.746","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.2.746","url":null,"abstract":"Numerical simulation of high enthalpy flow in the nozzle of wind tunnel VAT-104 is carried out using a detailed model of nonequilibrium physical and chemical processes. An implicit staggered-grid scheme of the second order of accuracy is used to approximate the governing equations. The goals of this modeling are: (1) to test a numerical approach to simulate high temperature nonequilibrium flows, (2) to determine the role of processes important for energy exchange at the nozzle flow conditions, (3) to get numerical values of species mass fractions and molecule vibration temperatures along the nozzle and at the entry to the test part. The illustrations below show the profile of VAT-104 nozzle, the difference scheme stencils, the N and N 2 mass fraction profiles and vibration temperatures profiles along the nozzle.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116243939","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/PHCHGD.19.2.742
Y. Tunik, G. Gerasimov
The detonation capacity of kerosene vapor is numerically studied in supersonic flow around a circular cylinder with an end windward wall. The model of kerosene combustion in the air takes into account 68 reactions for 44 components. Its testing is made by the way of comparison with the available calculated and experimental data on the ignition delay time under adiabatic conditions at a constant density. The mathematical model flow past cylinder is based on twodimensional non-stationary Euler equations for a multi-component reacting gas. The enthalpy and entropy of the initial mixture and combustion products are determined by polynomials from the NASA base. Calculations are performed on the basis of the Godunov finite-difference scheme and its modification of increased accuracy. The results allow justifying the parameters of the nozzle with a central body for a supersonic direct-flow chamber with detonative combustion of kerosene.
{"title":"Ignition of kerosene vapor in supersonic flow around a cylinder with an end windward wall","authors":"Y. Tunik, G. Gerasimov","doi":"10.33257/PHCHGD.19.2.742","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.2.742","url":null,"abstract":"The detonation capacity of kerosene vapor is numerically studied in supersonic flow around a circular cylinder with an end windward wall. The model of kerosene combustion in the air takes into account 68 reactions for 44 components. Its testing is made by the way of comparison with the available calculated and experimental data on the ignition delay time under adiabatic conditions at a constant density. The mathematical model flow past cylinder is based on twodimensional non-stationary Euler equations for a multi-component reacting gas. The enthalpy and entropy of the initial mixture and combustion products are determined by polynomials from the NASA base. Calculations are performed on the basis of the Godunov finite-difference scheme and its modification of increased accuracy. The results allow justifying the parameters of the nozzle with a central body for a supersonic direct-flow chamber with detonative combustion of kerosene.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"39 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123550128","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/phchgd.19.2.743
E. Gurentsov, A. Eremin, Stanislav Musikhin, R. Kolotushkin, D. Khmelenin, Y. Grigoriev
{"title":"Regularities in the Formation of Metal-Carbon Nanoparticles during Pyrolysis and Photolysis of Gaseous Compaunds","authors":"E. Gurentsov, A. Eremin, Stanislav Musikhin, R. Kolotushkin, D. Khmelenin, Y. Grigoriev","doi":"10.33257/phchgd.19.2.743","DOIUrl":"https://doi.org/10.33257/phchgd.19.2.743","url":null,"abstract":"","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130700261","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/PHCHGD.19.2.744
A. Kroupnov, M. Pogosbekian
{"title":"Quantum mechanical simulation of the direct mechanism for exchange reaction СО + N2O <-> СO2+N2","authors":"A. Kroupnov, M. Pogosbekian","doi":"10.33257/PHCHGD.19.2.744","DOIUrl":"https://doi.org/10.33257/PHCHGD.19.2.744","url":null,"abstract":"","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132409442","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/phchgd.19.2.753
A. Molchanov, V. E. Popov
A method for calculating high-altitude jets exhausting into a rarefied gas has been developed. This method is based on the use of quasi-gas-dynamic (QGD) equations. The solution of quasi-gasdynamic equations requires the use of significantly smaller computer resources as compared with the methods of direct numerical simulation. The equations of the continuity of gas mixture components and the equations for vibrational energies transfer in the quasi-gas-dynamic formulation were obtained from the Boltzmann equation. It was shown that when calculating with the use of QGD, the radiation intensity is significantly lower than when calculating the standard system of Navier‒Stokes equations (NS). This is due to the decrease in temperature (translational, rotational and vibrational) in the mixing layer.
{"title":"Calculation of Gas Dynamics and Radiation of High-Altitude Jets","authors":"A. Molchanov, V. E. Popov","doi":"10.33257/phchgd.19.2.753","DOIUrl":"https://doi.org/10.33257/phchgd.19.2.753","url":null,"abstract":"A method for calculating high-altitude jets exhausting into a rarefied gas has been developed. This method is based on the use of quasi-gas-dynamic (QGD) equations. The solution of quasi-gasdynamic equations requires the use of significantly smaller computer resources as compared with the methods of direct numerical simulation. The equations of the continuity of gas mixture components and the equations for vibrational energies transfer in the quasi-gas-dynamic formulation were obtained from the Boltzmann equation. It was shown that when calculating with the use of QGD, the radiation intensity is significantly lower than when calculating the standard system of Navier‒Stokes equations (NS). This is due to the decrease in temperature (translational, rotational and vibrational) in the mixing layer.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"235 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131668721","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2018-06-18DOI: 10.33257/phchgd.19.2.741
S. Denisikhin, V. N. Emel’yanov, K. Volkov, I. Teterina
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 computational mesh, and their reconstruction 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 parameters in the pre-nozzle volume corresponding to the outflow of the combustion products from the cylindrical channel and starshaped channel are compared, as well as the solutions of the problem obtained in quasistationary and unsteady formulations. The effects of the channel shape on the distribution of flow parameters and formation of a vortex flow structure in the nozzle block are discussed.
{"title":"Numerical simulation of gas-dynamics processes in thrust vectorable nozzle","authors":"S. Denisikhin, V. N. Emel’yanov, K. Volkov, I. Teterina","doi":"10.33257/phchgd.19.2.741","DOIUrl":"https://doi.org/10.33257/phchgd.19.2.741","url":null,"abstract":"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 computational mesh, and their reconstruction 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 parameters in the pre-nozzle volume corresponding to the outflow of the combustion products from the cylindrical channel and starshaped channel are compared, as well as the solutions of the problem obtained in quasistationary and unsteady formulations. The effects of the channel shape on the distribution of flow parameters and formation of a vortex flow structure in the nozzle block are discussed.","PeriodicalId":309290,"journal":{"name":"Physical-Chemical Kinetics in Gas Dynamics","volume":"83 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123969727","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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