Numerical Simulation of Transient Hypersonic Flow with Real Gas Effects PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Numerical Simulation of Transient Hypersonic Flow with Real Gas Effects PDF full book. Access full book title Numerical Simulation of Transient Hypersonic Flow with Real Gas Effects by Yanbao Ma. Download full books in PDF and EPUB format.
Author: Yanbao Ma
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Yanbao Ma
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 33
Get Book Here
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: Jean-Antoine Desideri
Publisher: Springer
ISBN: 9783540544289
Category : Science
Languages : en
Pages : 268
Get Book Here
Book Description
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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 56
Get Book Here
Book Description
The objective of this research is to conduct DNS studies of hypersonic boundary layer receptivity, transient growth and transition with surface roughness. The main approach is to use DNS as a research tool to study the boundary layer receptivity and transient-growth mechanisms in hypersonic flows, including the development of numerical algorithms and parallel computer codes of higher order numerical methods for the simulation of hypersonic flows with surface roughness of finite heights. During the three-year period, we have conducted DNS studies on the hypersonic boundary layer flows over flat plates and blunt cones. A new high-order cut-cell method has been developed for the numerical simulation of hypersonic boundary layer transition with finite height surface roughness. The method has been applied to the numerical simulations of two-dimensional hypersonic flows over a flat plate. Furthermore, the stabilization effect of the surface porous coating over a flat plate is extensively studied by series of numerical simulations. We also collaborate with Prof. Tumin in the University of Arizona to compare numerical and theoretical results on receptivity of a Mach 5.92 flow over a flat plate to wall blowing-suction, and to analyze the nonparallel flow effect.
Author: S. Riedelbauch
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
Get Book Here
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: Xiaolin Zhong
Publisher:
ISBN:
Category :
Languages : en
Pages : 31
Get Book Here
Book Description
The goal of this research project is to develop new advanced numerical methods and to perform direct numerical simulation (DNS) studies of transient hypersonic reacting flows over full 3-D maneuvering vehicles. The DNS tools and supporting theoretical approaches are used to gain new fundamental understanding of transition phenomena of 3-D chemically-reacting hypersonic boundary layers. Our research accomplishments in the report period can be classified into three areas. First, we have developed and validated new efficient and high-order accurate numerical methods for the DNS of 3-D hypersonic reacting boundary layers. The new methods include high-order semi-implicit Runge-Kutta schemes and new upwind high-order finite-difference shock-fitting schemes. These new methods were developed in order to overcome the difficulties associated with the DNS of hypersonic reacting flows with shock waves. Second, we have conducted extensive studies on the stability and receptivity phenomena of hypersonic boundary layers over blunt leading edges and elliptical cross-section blunt cones both by direct numerical simulation and by linear stability analyses. Third, the effects of using Burnett equations for rarefied hypersonic flow computations were investigated.
Author: S. Riedelbauch
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: Bertin
Publisher: Springer Science & Business Media
ISBN: 1461203716
Category : Science
Languages : en
Pages : 280
Get Book Here
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: Jun Kyu Lee
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Space vehicles that enter the atmosphere require the use of a Thermal Protection System (TPS) to protect them from aerodynamic heating. The TPS currently in use is composed of a heat-resistant material to protect the inner part of the vehicle, and it adds tremendously to the cost of a space mission. In contrast, it has been pointed out that such a high enthalpy gas flow, which is partially ionized, could be controlled through an electromagnetic effect, and as a result, the high convective heat could be reduced, and furthermore, the aerodynamic force acting on the vehicle could be controlled. A lot of research has been carried out, not only theoretically but also experimentally, to understand the electromagnetic effect. However, numerical accuracy in predicting these effects, especially for heat flux mitigation, has not been satisfactory. Accurate simulation of such flows requires the solution of the Navier-Stokes equations for compressible viscous flow, and for the equations describing the state of the high temperature gas containing many species in chemical and thermal equilibrium or non-equilibrium. In addition, Maxwell's equations for including the effects of electromagnetic fields upon an ionized hypersonic flow through Lorentz forces and Joule heating need to be solved in order to realize flow control advantages. Inclusion of these three sets of equations in the numerical simulation of hypersonic flow is computationally intensive and stiff to solve. Therefore, many researchers have made a number of simplifications based on certain assumptions to reduce the size of the governing equations. However, these simplifications and assumptions are not valid under certain flight regimes and can lead to inaccurate estimates of heat flux to the vehicle. In this thesis, the full magneto fluid dynamics (MFD) equations, including multi-species, chemical reactions, and Maxwell's equations, have been solved. The approach includes formulation of the full governing equations, the boundary conditions including catalytic, cold wall boundaries, and the numerical procedure for solving the governing equations. The solver is verified and validated with experimental data provided by Ziemer for shock stand-off distance, by Gulhan et al. and Kawamura et al. for heat flux mitigation. The numerical results show an excellent match with previously published experimental data.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Get Book Here
Book Description
A method for solving the viscous hypersonic flow field around realistic configurations is presented. The numerical procedure for generating the required finite difference grid and the two-factored implicit flow solver are described. Results are presented for the shuttle orbiter and a generic wing-body configuration at hypersonic Mach numbers.
