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Author: Edisson Sávio de Góes Maciel
Publisher: LAP Lambert Academic Publishing
ISBN: 9783659705410
Category :
Languages : en
Pages : 340
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Book Description
This book was written to students and engineers that like the Computational Fluid Dynamics (CFD) area; in other words, that like of programming algorithms to the resolution of physical problems. Some familiarity with code programming is required. The applications of this book aim aerospace problems. This book presents the chemical and thermochemical non-equilibrium conditions applied to Earth reentry and Mars entry flows. The five and seven species chemical models for the Earth reentry are implemented according to the law of mass action and Arrehnius formula. Moreover, vibrational contribution is also taken into account. The transport properties are calculated by the use of collision integral techniques. The nine species chemical model for the Mars entry uses the Wilke formula to obtain the transport properties. Vibrational contribution also takes into account Millikhan and White formula and Park's correction above 8,000 K. Two and three-dimensional spaces are considered. The Van Leer and Liou and Steffen Jr. schemes are employed. Good results are obtained in both studies. A finite volume formulation and structured and unstructured spatial discretizations are employed.
Author: Edisson Sávio de Góes Maciel
Publisher: LAP Lambert Academic Publishing
ISBN: 9783659705410
Category :
Languages : en
Pages : 340
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Book Description
This book was written to students and engineers that like the Computational Fluid Dynamics (CFD) area; in other words, that like of programming algorithms to the resolution of physical problems. Some familiarity with code programming is required. The applications of this book aim aerospace problems. This book presents the chemical and thermochemical non-equilibrium conditions applied to Earth reentry and Mars entry flows. The five and seven species chemical models for the Earth reentry are implemented according to the law of mass action and Arrehnius formula. Moreover, vibrational contribution is also taken into account. The transport properties are calculated by the use of collision integral techniques. The nine species chemical model for the Mars entry uses the Wilke formula to obtain the transport properties. Vibrational contribution also takes into account Millikhan and White formula and Park's correction above 8,000 K. Two and three-dimensional spaces are considered. The Van Leer and Liou and Steffen Jr. schemes are employed. Good results are obtained in both studies. A finite volume formulation and structured and unstructured spatial discretizations are employed.
Author: Edisson Sávio de Góes Maciel
Publisher: LAP Lambert Academic Publishing
ISBN: 9783659697586
Category :
Languages : en
Pages : 696
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Book Description
This book was written to students and engineers that like the Computational Fluid Dynamics (CFD) area; in other words, that like of programming algorithms to the resolution of physical problems. Some familiarity with code programming is required. However, through the computation courses teaching at the Universities the engineering student and common areas will have the capacity of programming the codes presented in this book and much more of his/her interest. The applications of this book aim aerospace problems. This book presents the chemical and thermochemical non-equilibrium conditions applied to Earth reentry flows. The five, seven, and eleven species chemical models are implemented according to the law of mass action and Arrehnius formula. Moreover, vibrational contribution is also taken into account, with the characteristic vibrational time calculated by Millikhan and White formula, corrected by Park's model above 8,000 K. The transport properties are calculated by collision integral techniques. The Van Leer and Liou and Steffen Jr. schemes are employed. First-order and TVD results are obtained. A finite volume formulation and structured spatial discretization are employed.
Author: Bertin
Publisher: Springer Science & Business Media
ISBN: 1461203716
Category : Science
Languages : en
Pages : 280
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Book Description
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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 33
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Book Description
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.
Author: Marvin I. Kussoy
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
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Author: Robert William MacCormack
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 42
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Book Description
The present paper presents an efficient algorithm for solving the unsteady Navier-Stokes equations. It is a line Gauss-Seidel relaxation implicit algorithm for three-dimensional flow. Such algorithms have shown very fast convergence properties for two-dimensional flow. The extension to three- dimensions a been troublesome. The proposed algorithm presented herein was developed to solve these difficulties. A computer program based upon this algorithm has been written to solve two-dimensional plane symmetric, axisymmetric or three-dimensional flow of a perfect gas, or a real gas model for air with five species (N2, 02, NO, N, 0) or seven species (N2, 02, NO, NO+, N, 0, e- ). The program can simulate a gas in thermal equilibrium or in thermal nonequilibrium with two temperatures (Translational-Rotational and Vibrational) or three temperatures (Translational, Rotational, and Vibrational). Convergence to engineering accuracy is generally achieved in under a hundred time steps for both two- and three-dimensional flow. Provision is made within the program for a one or two equation turbulence model. Applications are presented to verify the code by comparison with experiment and flight tests. Finally, the numerically simulated flow about a hypersonic vehicle at Mach 25 in powered flight is presented.
Author: Michael Pfitzner
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages :
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Author: S. Riedelbauch
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
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.
Author: Roberto Vaglio-Laurin
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 54
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Author: J. E. Bardina
Publisher:
ISBN:
Category :
Languages : en
Pages :
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