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Numerical Simulation Of Hypersonic Rarefied Flows Using The Second Order Constitutive Model Of The Boltzmann Equation
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Book Synopsis Numerical Simulation of Hypersonic Rarefied Flows Using the Second-Order Constitutive Model of the Boltzmann Equation by : Rho Shin Myong
Download or read book Numerical Simulation of Hypersonic Rarefied Flows Using the Second-Order Constitutive Model of the Boltzmann Equation written by Rho Shin Myong and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Various mathematical theories and simulation methods were developed in the past for describing gas flows in nonequilibrium, in particular, hypersonic rarefied regime. They range from the mesoscale models like the Boltzmann equation, the DSMC, and the high-order hydrodynamic equations. The moment equations can be derived by introducing the statistical averages in velocity space and then combining them with the Boltzmann kinetic equation. In this chapter, on the basis of Eu's generalized hydrodynamics and the balanced closure recently developed by Myong, the second-order constitutive model of the Boltzmann equation applicable for numerical simulation of hypersonic rarefied flows is presented. Multi-dimensional computational models of the second-order constitutive equations are also developed based on the concept of decomposition and method of iterations. Finally, some practical applications of the second-order constitutive model to hypersonic rarefied flows like re-entry vehicles with complicated geometry are described.
Book Synopsis Advances in Some Hypersonic Vehicles Technologies by : Ramesh K. Agarwal
Download or read book Advances in Some Hypersonic Vehicles Technologies written by Ramesh K. Agarwal and published by BoD – Books on Demand. This book was released on 2018-03-14 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book describes the recent progress in some hypersonic technologies such as the aerodynamic modeling and numerical simulations of rarefied flows, boundary layer receptivity, coupled aerodynamics, and heat transfer problems, including fluid-thermal-structure interactions and launcher aerodynamic design as well as other miscellaneous topics, such as porous ceramic composite phase change control system and vehicle profile, following LQR design. Both the researchers and the students should find the material useful in their work.
Download or read book Advances in Hypersonics written by BERTIN and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 438 pages. Available in PDF, EPUB and Kindle. Book excerpt: These three volumes entitled Advances in Hypersonics contain the Proceedings of the Second and Third Joint US/Europe Short Course in Hypersonics which took place in Colorado Springs and Aachen. The Second Course was organized at the US Air Force Academy, USA in January 1989 and the Third Course at Aachen, Germany in October 1990. The main idea of these Courses was to present to chemists, com puter scientists, engineers, experimentalists, mathematicians, and physicists state of the art lectures in scientific and technical dis ciplines including mathematical modeling, computational methods, and experimental measurements necessary to define the aerothermo dynamic environments for space vehicles such as the US Orbiter or the European Hermes flying at hypersonic speeds. The subjects can be grouped into the following areas: Phys ical environments, configuration requirements, propulsion systems (including airbreathing systems), experimental methods for external and internal flow, theoretical and numerical methods. Since hyper sonic flight requires highly integrated systems, the Short Courses not only aimed to give in-depth analysis of hypersonic research and technology but also tried to broaden the view of attendees to give them the ability to understand the complex problem of hypersonic flight. Most of the participants in the Short Courses prepared a docu ment based on their presentation for reproduction in the three vol umes. Some authors spent considerable time and energy going well beyond their oral presentation to provide a quality assessment of the state of the art in their area of expertise as of 1989 and 1991.
Book Synopsis Numerical Studies of Low-Density Two-Dimensional Hypersonic Flows by Using the Navier-Stokes and Burnett Equations with Nonequilibrium Real Gas Effects by :
Download or read book Numerical Studies of Low-Density Two-Dimensional Hypersonic Flows by Using the Navier-Stokes and Burnett Equations with Nonequilibrium Real Gas Effects written by and published by . This book was released on 1997 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: The goal of this research is to study the laminar turbulent transition and other transient flow phenomena of 3-D chemically reacting hypersonic boundary layers by direct numerical simulation (DNS) and by linear stability analysis. The research in the report period was focused on developing new numerical methods for such studies and studying several fundamental transient hypersonic flow phenomena. First, several new efficient and high-order accurate numerical methods for DNS of 3-D hypersonic reacting boundary layers and for computing unsteady hypersonic flows with complex shock interactions were developed. These new methods were developed in order to overcome difficulties associated with the direct numerical simulation of hypersonic flows. Second, several studies on the stability phenomena of hypersonic boundary layers over blunt leading edges both by direct numerical simulation and by linear stability analyses were performed. Also completed were extensive numerical studies on real gas effects on a steady shock/boundary layer interaction and a self-sustained unsteady shock-shock interference heating flows. Third, the effects of using Burnett equations for rarefied hypersonic flow computations were investigated. With the completion of the bulk of work on the development of new numerical methods for complex hypersonic flow simulation, the DNS studies are currently being extended to 3-D hypersonic boundary layer transition over elliptic cross section cones.
Book Synopsis Hypersonic Flows for Reentry Problems by : Jean-Antoine Desideri
Download or read book Hypersonic Flows for Reentry Problems written by Jean-Antoine Desideri and published by Springer. This book was released on 1992-01-17 with total page 268 pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the most challenging problems of modern engineering is undoubtedly the prediction of hypersonic flows around space vehicles in reentry conditions. Indeed, the difficulties are numerous: first of all, these flows are very difficult to model, since very complex physical and chemical phenomena take place during the reentry phase; secondly, temperature, velocity and enthalpy are very high and densities are very low, making the reentry process very difficult to reproduce in ground-based experiments. The past three decades have seen important efforts in computational fluid dynam ics relying on the use of supercomputers to simulate these very complicated flows. The numerical simulation based on imperfect models and methods which were es sentially designed for transonic and supersonic flows has still a long way to go in order to be able to predict these hypersonic reentry flows very accurately. This situation has motivated very strong international cooperative efforts with, as the most visible consequences, the EuropelUnited States Short Courses on Hy personics, which were held in Paris, in 1987 [1,2], Colorado Springs in 1989 [3], and Aachen in 1990 [3]. The workshop on Hypersonics whose results are presented and analysed in these volumes is also a direct consequence of this international cooperation. This scien tific event was an initiative of P. Perrier, Head of the Theoretical Aerodynamics Department of DASSAULT AVIATION, who played a key role in the identification of the critical problems and the realisation of experiments, within the Hermes R&D program framework.
Download or read book Advances in Hypersonics written by Bertin and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt: These three volumes entitled Advances in Hypersonics contain the Proceedings of the Second and Third Joint US/Europe Short Course in Hypersonics which took place in Colorado Springs and Aachen. The Second Course was organized at the US Air Force Academy, USA in January 1989 and the Third Course at Aachen, Germany in October 1990. The main idea of these Courses was to present to chemists, com puter scientists, engineers, experimentalists, mathematicians, and physicists state of the art lectures in scientific and technical dis ciplines including mathematical modeling, computational methods, and experimental measurements necessary to define the aerothermo dynamic environments for space vehicles such as the US Orbiter or the European Hermes flying at hypersonic speeds. The subjects can be grouped into the following areas: Phys ical environments, configuration requirements, propulsion systems (including airbreathing systems), experimental methods for external and internal flow, theoretical and numerical methods. Since hyper sonic flight requires highly integrated systems, the Short Courses not only aimed to give in-depth analysis of hypersonic research and technology but also tried to broaden the view of attendees to give them the ability to understand the complex problem of hypersonic flight. Most of the participants in the Short Courses prepared a docu ment based on their presentation for reproduction in the three vol umes. Some authors spent considerable time and energy going well beyond their oral presentation to provide a quality assessment of the state of the art in their area of expertise as of 1989 and 1991.
Book Synopsis Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the RPLUS2D Code by : Kamlesh Kapoor
Download or read book Numerical Simulation of Supersonic Compression Corners and Hypersonic Inlet Flows Using the RPLUS2D Code written by Kamlesh Kapoor and published by . This book was released on 1994 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Advances in Hypersonics: Computing hypersonic flows by : John J. Bertin
Download or read book Advances in Hypersonics: Computing hypersonic flows written by John J. Bertin and published by Birkhauser. This book was released on 1992 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Approximate Two Layer (Inviscid/Viscous) Methods to Model Aerothermodynamic Environments.- Second-Order Effects in Hypersonic Boundary Layers.- Unstructured-Grid Algorithms for High-Speed CFD Analysis.- Numerical Simulation of Three-Dimensional Hypersonic Viscous Flows.- Numerical Simulation of Entry Flow over Blunt Swept-Wing Planes.- Viscous Nonequilibrium Flow Calculations.- The Finite Pointset Method for Hypersonic Flows in the Rarefied Gas Regime.- Computation of Flowfields for Hypersonic Flight at High Altitudes.
Author :Jean-Antoine Desideri Publisher :Springer Science & Business Media ISBN 13 :3642765270 Total Pages :1231 pages Book Rating :4.6/5 (427 download)
Book Synopsis Hypersonic Flows for Reentry Problems by : Jean-Antoine Desideri
Download or read book Hypersonic Flows for Reentry Problems written by Jean-Antoine Desideri and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 1231 pages. Available in PDF, EPUB and Kindle. Book excerpt: This entry describes the experimental work conducted in the Department of Aeronautics at Imperial College in connection with Test Problems 1 and 2 of the "Workshop on Hypersonic Flows for Reentry Problems, Part I". These are defined as follows: Test Problem 1 Flow Over a Slender Cone Test Problem 2 Turbulent Base Flow The main requirement of this text is to present the experimental data for direct comparison with the predictions of CFD codes. We have therefore concentrated mainly on a factual statement of measuring techniques and results, together with an assessment of experimental accuracy. Future publications will be devoted to more extensive physical interpretations and discussions of the results. We have produced a large volume of data, some of which were categorised as "MANDATORY" and some as "OPTIONAL" for the purposes of CFD validation. However, only the "MANDATORY" data are presented here, although the other data are available and will be published separately later. 2. EXPERIMENTAL ARRANGEMENT 2. 1 The Test Facility The experiments were conducted in the Imperial College No. 2 Gun tunnel. This facility is a conventional intermittent blowdown tunnel with a contoured Mach 9 (nominal) axisymmetric nozzle fed by a free piston compression heater. The operating condition under which the data contained in this report were obtained is presented in Table 1. Test 2 T (oK) M b. Mlm Po (N/m ) Re/m T (oK) IX) IX) Case IX) w 1. 1 7 7 +0. 14 9. 16 6. 67x10 5. 5xl0 59.
Book Synopsis Theoretical and Numerical Studies of Rarefied Hypersonic Flows by : Xionghui Huang
Download or read book Theoretical and Numerical Studies of Rarefied Hypersonic Flows written by Xionghui Huang and published by . This book was released on 2014 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this dissertation a comprehensive work on theoretical and numerical studies of rarefied hypersonic flows is presented. On the theoretical part, gaskinetic study and exact solutions are obtained for problems related with high speed collisionless round jet: expanding into a vacuum; impinging at a normally set, diffuse or specular reflective plate with finite radius. Several fundamental geometry-velocity relations are utilized in this study and they play crucial roles. These complete results include flowfield properties, and impingement properties at the plate surface. The final results include complex but accurate integrations involving geometry and specific speed ratio factors. Severals numerical simulations with the direct simulation Monte Carlo method validate these analytical exact results. In the numerical part, a multi-dimensional gas-dynamical computational scheme package GRASP-K ("Generalized Rarefied gAs Simulation Package - Kinetic") is presented. This implementation adopts a concept of simulation engine and it utilizes many Object-Oriented Programming features and software engineering design patterns. As a result, this implementation successfully resolves the problem of functionality and interface conflictions for multi-dimension Gas Kinetic Scheme implementations. The package has an open architecture which benefits further development and code maintenance. This package can utilize traditional structured, unstructured or hybrid grids to model multi-dimensional complex geometries and multi-species hypersonic thermo-chemically non equilibrium gas flows. A preliminary test case of a two-species hypersonic flow passing a cylinder and some preliminary results are obtained. The pressure distribution of the gas mixture along the cylinder wall is compared with those in previous works. A Navier-Stokes equations based computational fluid dynamics solver is also incorporated in the package to simulate hypersonic nonequilibrium flows. This solver includes comprehensive chemical reaction models and thermodynamics relations and the phenolic-silica ablation flow simulation is considered. Finite rate chemical reactions, multiple temperature relaxation processes, and ionization phenomena are modeled. Hence the package can be used to simulate multiple-dimensional, non-equilibrium gas flows with multiple species. Simulation results of several hypersonic gas flows over blunted bodies are presented and compared with results in the literature.
Book Synopsis Numerical Simulation of 3D Rarefied Hypersonic Flows by : T.C. Lin
Download or read book Numerical Simulation of 3D Rarefied Hypersonic Flows written by T.C. Lin and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis On the Numerical Simulation of Three-Dimensional Hypersonic Flow by : S. Riedelbauch
Download or read book On the Numerical Simulation of Three-Dimensional Hypersonic Flow written by S. Riedelbauch and published by . This book was released on 1987 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: A report on the first steps towards the numerical simulation of hypersonic flows. Intentionally, the ideal-gas assumption is used to validate the methods by comparing results with experimentally observed or theoretically obtained data in cold hypersonic flows about simple geometries. The approaches cover the continuum as well as the gas-kinetic flow regime. An implicit finite-difference method with bow-shock fitting is employed to integrate the time-dependent Navier-Stokes equations, while the gas-kinetic flow is simulated by approximations to Boltzmann's equation. The Direct-Simulation Monte-Carlo method is preferred to the Molecular-Dynamics approach because of its larger computational efficiency. Results are compared with experimental data for the laminar flow past a blunted cone at M = 10.6 and past a hemisphere at M = 4.15. The decay of Oseen's vortex at Kn = 0.1, and the gas-kinetic flow past a cylinder at M = 5.48 with Kn = 0.1 and 0.3 have been simulated, and results are shown in comparison with theoretical data. As an application to more realistic configurations the three-dimensional laminar flow past the noise of a typical spacecraft and the gas-kinetic flow in the symmetry plane of the flow past the same configuration is being discussed. The next steps will include real-gas modelling. For hot hypersonic flows experimental data are badly needed for comparison purpose.
Book Synopsis Numerical Simulation of Chemically Reactive Hypersonic Flows by : Sanjeev Kumar
Download or read book Numerical Simulation of Chemically Reactive Hypersonic Flows written by Sanjeev Kumar and published by . This book was released on 2006 with total page 131 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Development and Computation of Continuum Higher Order Constitutive Relations for High-altitude Hypersonic Flow by : Stanford University. Department of Aeronautics and Astronautics
Download or read book Development and Computation of Continuum Higher Order Constitutive Relations for High-altitude Hypersonic Flow written by Stanford University. Department of Aeronautics and Astronautics and published by . This book was released on 1991 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Flows for Reentry Problems by : Jean-Antoine Desideri
Download or read book Hypersonic Flows for Reentry Problems written by Jean-Antoine Desideri and published by Springer. This book was released on 1992-01-17 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the most challenging problems of modern engineering is undoubtedly the prediction of hypersonic flows around space vehicles in reentry conditions. Indeed, the difficulties are numerous: first of all, these flows are very difficult to model, since very complex physical and chemical phenomena take place during the reentry phase; secondly, temperature, velocity and enthalpy are very high and densities are very low, making the reentry process very difficult to reproduce in ground-based experiments. The past three decades have seen important efforts in computational fluid dynam ics relying on the use of supercomputers to simulate these very complicated flows. The numerical simulation based on imperfect models and methods which were es sentially designed for transonic and supersonic flows has still a long way to go in order to be able to predict these hypersonic reentry flows very accurately. This situation has motivated very strong international cooperative efforts with, as the most visible consequences, the EuropelUnited States Short Courses on Hy personics, which were held in Paris, in 1987 [1,2], Colorado Springs in 1989 [3], and Aachen in 1990 [3]. The workshop on Hypersonics whose results are presented and analysed in these volumes is also a direct consequence of this international cooperation. This scien tific event was an initiative of P. Perrier, Head of the Theoretical Aerodynamics Department of DASSAULT AVIATION, who played a key role in the identification of the critical problems and the realisation of experiments, within the Hermes R&D program framework.
Book Synopsis Hypersonic Flows for Reentry Problems by : Jean-Antoine Desideri
Download or read book Hypersonic Flows for Reentry Problems written by Jean-Antoine Desideri and published by Springer. This book was released on 2011-12-15 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the most challenging problems of modern engineering is undoubtedly the prediction of hypersonic flows around space vehicles in reentry conditions. Indeed, the difficulties are numerous: first of all, these flows are very difficult to model, since very complex physical and chemical phenomena take place during the reentry phase; secondly, temperature, velocity and enthalpy are very high and densities are very low, making the reentry process very difficult to reproduce in ground-based experiments. The past three decades have seen important efforts in computational fluid dynam ics relying on the use of supercomputers to simulate these very complicated flows. The numerical simulation based on imperfect models and methods which were es sentially designed for transonic and supersonic flows has still a long way to go in order to be able to predict these hypersonic reentry flows very accurately. This situation has motivated very strong international cooperative efforts with, as the most visible consequences, the EuropelUnited States Short Courses on Hy personics, which were held in Paris, in 1987 [1,2], Colorado Springs in 1989 [3], and Aachen in 1990 [3]. The workshop on Hypersonics whose results are presented and analysed in these volumes is also a direct consequence of this international cooperation. This scien tific event was an initiative of P. Perrier, Head of the Theoretical Aerodynamics Department of DASSAULT AVIATION, who played a key role in the identification of the critical problems and the realisation of experiments, within the Hermes R&D program framework.
Book Synopsis Effects of Thermochemical Nonequilibrium on Hypersonic Boundary-Layer Instability in the Presence of Surface Ablation Or Isolated Two-Dimensional Roughness by : Clifton Mortensen
Download or read book Effects of Thermochemical Nonequilibrium on Hypersonic Boundary-Layer Instability in the Presence of Surface Ablation Or Isolated Two-Dimensional Roughness written by Clifton Mortensen and published by . This book was released on 2015 with total page 251 pages. Available in PDF, EPUB and Kindle. Book excerpt: The current understanding of the effects of thermochemical nonequilibrium on hypersonic boundary-layer instability still contains uncertainties, and there has been little research into the effects of surface ablation, or two-dimensional roughness, on hypersonic boundary-layer instability. The objective of this work is to study the effects of thermochemical nonequilibrium on hypersonic boundary-layer instability. More specifically, two separate nonequilibrium flow configurations are studied: 1) flows with graphite surface ablation, and 2) flows with isolated two-dimensional surface roughness. These two flow types are studied numerically and theoretically, using direct numerical simulation and linear stability theory, respectively. To study surface ablation, a new high-order shock-fitting method with thermochemical nonequilibrium and finite-rate chemistry boundary conditions for graphite ablation is developed and validated. The method is suitable for direct numerical simulation of boundary-layer transition in a hypersonic real-gas flow with graphite ablation. The new method is validated by comparison with three computational data sets and one set of experimental data. Also, a thermochemical nonequilibrium linear stability theory solver with a gas phase model that includes multiple carbon species, as well as a linearized surface graphite ablation model, is developed and validated. It is validated with previously published linear stability analysis and direct numerical simulation results. A high-order method for discretizing the linear stability equations is used which can easily include high-order boundary conditions. The developed codes are then used to study hypersonic boundary-layer instability for a 7 deg half angle blunt cone at Mach 15.99 and the Reentry F experiment at 100~kft. Multiple simulations are run with the same geometry and freestream conditions to help separate real gas, blowing, and carbon species effects on hypersonic boundary-layer instability. For the case at Mach 15.99, a directly simulated 525~kHz second-mode wave was found to be significantly unstable for the real-gas simulation, while in the ideal-gas simulations, no significant flow instability is seen. An N factor comparison also shows that real-gas effects significantly destabilize the flow when compared to an ideal gas. Blowing is destabilizing for the real gas simulation and has a negligible effect for the ideal gas simulation due to the different locations of instability onset. Notably, carbon species resulting from ablation are shown to slightly stabilize the flow for both cases. For the Reentry F flow conditions, inclusion of the ablating nose cone was shown to increase the region of second mode growth near the nose cone. Away from the nose cone, the second mode was relatively unaffected. Experimental and numerical results have shown that two-dimensional surface roughness can stabilize a hypersonic boundary layer dominated by second-mode instability. It is sought to understand how this physical phenomenon extends from an airflow under a perfect gas assumption to that of a flow in thermochemical nonequilibrium. To these ends, a new high-order shock-fitting method that includes thermochemical nonequilibrium and a cut-cell method, to handle complex geometries unsuitable for structured body-fitted grids, is presented. The new method is designed specifically for direct numerical simulation of hypersonic boundary-layer transition in a hypersonic real-gas flow with arbitrary shaped surface roughness. The new method is validated and shown to perform comparably to a high-order method with a body-fitted grid. For a Mach 10 flow over a flat plate, a two-dimensional roughness element was found to stabilize the second mode when placed downstream of the synchronization location. This result is consistent with previous results for perfect-gas flows. For a Mach 15 flow over a flat plate, a two-dimensional surface roughness element stabilizes the second-mode instability more effectively in a thermochemical nonequilibrium flow, than in a corresponding perfect gas flow.
