Classic and High-Enthalpy Hypersonic Flows presents a complete look at high-enthalpy hypersonic flow from a review of classic theories to a discussion of future advances centering around the Born-Oppenheim approximation, potential energy surface, and critical point for transition. The state-of-the-art hypersonic flows are defined by a seamless integration of the classic gas dynamic kinetics with nonequilibrium chemical kinetics, quantum transitions, and radiative heat transfer. The book is intended for graduate students studying advanced aerodynamics and taking courses in hypersonic flow. It can also serve as a professional reference for practicing aerospace and mechanical engineers of high-speed aerospace vehicles and propulsion system research, design, and evaluation. Features Presents a comprehensive review of classic hypersonic flow from the Newtonian theory to blast wave analogue. Introduces nonequilibrium chemical kinetics to gas dynamics for hypersonic flows in the high-enthalpy state. Integrates quantum mechanics to high-enthalpy hypersonic flows including dissociation and ionization. Covers the complete heat transfer process with radiative energy transfer for thermal protection of earth reentry vehicle. Develops and verifies the interdisciplinary governing equations for understanding and analyzing realistic hypersonic flows.
The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.
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.
Progress in Astronautics and Rocketry, Volume 7: Hypersonic Flow Research compiles papers presented at a conference on hypersonics held at the Massachusetts Institute of Technology in August 1961. This book discusses the low Reynolds number effects, chemical kinetics effects, inviscid flow calculations, and experimental techniques relating to the problems in acquiring an understanding of hypersonic flow. The structure and composition of hypersonic wakes with attendant complex chemical kinetic effects is only briefly mentioned. This text consists of five parts. Parts A to C comprise of theoretical papers on the problems of calculating flow fields at hypersonic speeds. The experimental techniques that are of immediate practical interest in view of the difficulty of flight testing are discussed in Parts D and E. This publication is beneficial to engineers involved in advanced design problems.
Introduction to Hypersonic Flow has been made available to the English speaking reader because of its usefulness for those individuals desirous of obtaining an introduction to the subject. Written by an internationally acknowledged expert in the field of hypersonic flow, the book makes available heretofore unpublished Soviet work, as well as published work little known outside the Soviet Union. The author has however made every effort to include, where appropriate. Western references for the work he discusses. Starting with a general introductory chapter on hypersonic aerodynamics and aerodynamic problems, the remainder of the book concentrates on the inviscid, perfect fluid aspects of hypersonic flow, with emphasis on the fundamental concepts and rational methods of calculation. The book is directed to students of aerodynamics and gas dynamics, as well as to scientists and engineers interested in problems of hypersonic flight. The level of approach is such that it should prove particularly useful as an undergraduate and introductory graduate text.
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.
Hypersonic high enthalpy separated flows over two configurations, a rearward facing step and a compression corner were numerically investigated using computational fluid dynamics (CFD). Separated flow over the rearward facing step was studied at two enthalpies, 26 MJ/kg and 50 MJ/kg, corresponding to suborbital and superorbital speeds. The shock wave/boundary layer interaction and separation at the compression corner were studied at low and moderate enthalpies of 3 MJ/kg and 20 MJ/kg respectively. The numerical results have been compared to the available experimental data obtained in the X2 expansion tube facility which generates suborbital and superorbital speeds. The compression corner experimental data was obtained in the T3 free piston driven shock tunnel. In both these studies the flow medium was air. Two CFD codes, MB-CNS-2 and Eilmer-3, which primarily solve time-accurate Navier-Stokes equations were used to investigate the flow fields utilising AUSMDV flux splitting method. The perfect gas and chemical nonequilibrium calculations used MB-CNS-2, and the chemical plus thermal nonequilibrium, Eilmer-3. The chemical nonequilibrium behaviour of the gas was based on Gupta's kinetic scheme, whereas the thermo-chemical nonequilibrium was based on Park's two-temperature model. The computational flow establishments over attached and separated flows under suborbital and superorbital conditions suggested that the flow requires a longer time to establish than was available for testing in the X2 facility. Heat flux comparisons with experiments over the flat plate showed fair agreement and indicated that the boundary layer was essentially chemically and thermally frozen. In the close vicinity of the step, the presence of the Goldstein Singularity over the lip was observed and separation occurred on the face of the step. The separation moved further down the face with decrease in Reynolds number. A pressure minimum was shown to develop close to the location of separation as a result of over expansion followed by a recompression to the base pressure through a lip shock. Between separation and reattachment, the effects of chemical reactions were found to be negligible and the species were essentially frozen. A small region of thermal equilibrium prevailed close to the bottom corner of the step. Downstream of the step, the computed heat flux showed reasonable agreement with experiments. Computations with a rounded corner step configuration showed an increase in heat flux, skin friction and pressure between separation and reattachment with the increase in corner radius. In particular, the base pressure increased by nearly 30% for a fully rounded corner compared with a sharp corner in suborbital flow, while, in superorbital flow, it increased by a factor of 10. The increase in base pressure with increase in corner radius appears to be due, firstly, to the decrease in the strength of the expansion (resulting in a less steeper fall in pressure) and secondly, due to the formation of the recompression shock nearer to the base. The effects of chemistry were again found to be insignificant in the separated region. Computed flow visualisations showed that the shear layer at separation gradually became parallel to the plate as the radius increased. The compression corner results for the higher enthalpy flow showed that the separation, reattachment and recirculation regions were affected by chemical reactions. The heat flux and pressure comparisons with experiments for attached, incipiently separated and fully separated flows, suggested that CFD can reasonably predict the laminar shock boundary/layer interaction in the separated region at the corner. Significant differences were noted downstream over the ramp surface, particularly in regard to both locations and magnitudes of the peak heat flux and pressure and in the subsequent distributions of both heat flux and pressure. Under low enthalpy conditions, a similar situation was noted but chemical reactions were insignificant. The Eilmer-3 code was also used on the well known double cone configuration and the results were compared with the bench mark experimental data and previous CFD simulations based on steady solutions. The comparison of the present CFD data with these previous CFD and experimental data was fair at best highlighting not only the need for refined grids but also the difference between the time dependent and steady state approaches.
Hypersonic Flow Theory presents the fundamentals of fluid mechanics, focusing on the hypersonic flow theory and approaches in theoretical aerodynamics. This book discusses the assumptions underlying hypersonic flow theory, unified supersonic-hypersonic similitude, two-dimensional and axisymmetric bodies, and circular cylinder. The constant-streamtube-area approximation, streamtube-continuity methods, and tangent-wedge and tangent-cone are also deliberated. This text likewise covers the similar laminar boundary layer solutions, bluntness induced interactions on slender bodies, and free molecule transfer theory. The dynamics of hypersonic flight or hypersonic wing theory, magnetohydrodynamic theory, or any developments involving treatment of the Boltzmann equation are not included. This publication is intended for hypersonic aerodynamicists, students, and researchers conducting work on the hypersonic flow phenomena.
