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Non Equilibrium Chemistry Effects On Hypersonic Separated Flows Shock Wave Boundary Layer Interaction
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Book Synopsis Non-Equilibrium Chemistry Effects on Hypersonic Separated Flows--Shock- Wave/Boundary-Layer Interaction by :
Download or read book Non-Equilibrium Chemistry Effects on Hypersonic Separated Flows--Shock- Wave/Boundary-Layer Interaction written by and published by . This book was released on 1990 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has addressed the question: What is the effect of nonequilibrium chemical reactions on separated hypersonic flow? The model used to generate the separate flow is a hypersonic shock wave/boundary layer interaction on a flat plate in a high enthalpy flow. The flow was calculated by means of a finite-difference, time-marching solution. The results show that nonequilibrium effects can be important in the separated flow region, and that future applications should be aware of such effects. Keywords: Separated flow, Non-equilibrium, Shock-wave/boundary layer, Boundary layer interaction.
Book Synopsis Shock Strength Effects on Separated Flows in Non-equilibrium Chemically Reacting Air Shock Wave/boundary Layer Interaction by : Charles A. Ballaro
Download or read book Shock Strength Effects on Separated Flows in Non-equilibrium Chemically Reacting Air Shock Wave/boundary Layer Interaction written by Charles A. Ballaro and published by . This book was released on 1991 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Radiation Effects on Hypersonic Flow in Non-equilibrium Chemically Reacting Air by : Yu-Hang Zhu
Download or read book Radiation Effects on Hypersonic Flow in Non-equilibrium Chemically Reacting Air written by Yu-Hang Zhu and published by . This book was released on 1992 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Shock Wave-Boundary-Layer Interactions by : Holger Babinsky
Download or read book Shock Wave-Boundary-Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Book Synopsis Viscous Hypersonic Flow by : William H. Dorrance
Download or read book Viscous Hypersonic Flow written by William H. Dorrance and published by Courier Dover Publications. This book was released on 2017-05-22 with total page 353 pages. Available in PDF, EPUB and Kindle. Book excerpt: Designed for advanced undergraduate and graduate courses in modern boundary-layer theory, this frequently cited work offers a self-contained treatment of theories for treating laminar and turbulent boundary layers of reacting gas mixtures. 1962 edition.
Book Synopsis Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds by : Awatef Hamed
Download or read book Flow Separation in Shock Wave Boundary Layer Interactions at Hypersonic Speeds written by Awatef Hamed and published by . This book was released on 1990 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Interaction of Chemistry, Turbulence, and Shock Waves in Hypervelocity Flow by : Graham V. Candler
Download or read book Interaction of Chemistry, Turbulence, and Shock Waves in Hypervelocity Flow written by Graham V. Candler and published by . This book was released on 1999 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: Significant contributions were made in a four-year interdisciplinary experimental, numerical and theoretical program to extend the state of knowledge and understanding of the effects of chemical reactions in hypervelocity flows. The program addressed the key problems in aerothermochemistry that arise from the interaction between the three strongly nonlinear effects: Compressibility; vorticity; and chemistry. Results included: (1) Discovery of dramatic damping effects of nonequilibrium vibration and chemistry on transition in hypervelocity flows; (2) Proper formulation of parameters for reacting blunt-body flows. (3) Effects of nonequilibrium chemistry in shock-on-shock interaction; (4) New experiments on, and correlation with theory of high-enthalpy flap-induced separation; (5) Computations of interaction of a shock wave with density interfaces and with compressible Hill's spherical vortex; (6) Extensive clarification of phenomena in supersonic shear flows using new diagnostic and computational tools; (7) New experiments and computations of hypervelocity double-one flow yielded insights into vibration-dissociation coupling; (8) First-principles computations of electron collision cross-sections with diatomic molecules and CO2; and (9) Development of new diagnostic technique LITA for accurate non-intrusive point measurement of gas properties.
Book Synopsis Effects of the Upstream Influence of a Shock Wave at Supersonic Speeds in the Presence of a Separated Boundary Layer by : Lloyd E. Daniels
Download or read book Effects of the Upstream Influence of a Shock Wave at Supersonic Speeds in the Presence of a Separated Boundary Layer written by Lloyd E. Daniels and published by . This book was released on 1954 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Shock-wave Shapes and Surface Pressures on Hemisphere- and Cone-cylinders in Low-density Hypersonic Flow Including Ablation by : Daryl J. Monson
Download or read book Shock-wave Shapes and Surface Pressures on Hemisphere- and Cone-cylinders in Low-density Hypersonic Flow Including Ablation written by Daryl J. Monson and published by . This book was released on 1970 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Also available online.
Book Synopsis A Study of Flow Separation in Regions of Shock Wave-boundary Layer Interaction in Hypersonic Flow by : Michael S. Holden
Download or read book A Study of Flow Separation in Regions of Shock Wave-boundary Layer Interaction in Hypersonic Flow written by Michael S. Holden and published by . This book was released on 1975 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interacting in the strong interaction regime. The flow is studied over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is strong and of fundamental importance to the problem. The theoretical analysis treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. A complementary experimental study investigated the flow over a flat plate-wedge compression surface for a range of free-stream Reynolds number and Mach number conditions in the strong interaction regime.
Book Synopsis Hypersonic Air Flow with Finite Rate Chemistry by :
Download or read book Hypersonic Air Flow with Finite Rate Chemistry written by and published by . This book was released on 1997 with total page 235 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this report, we present the results of a number of experimental studies and the accompanying analyses to develop and refine prediction techniques and the models that are employed in them to describe the effects of non-equilibrium flow chemistry, shock interaction, and turbulent mixing and combustion on the performance of vehicles and air breathing engines designed to fly in the hypersonic flow regime at velocities greater than 2 km/sec. During this research program, experimental studies and analyses were conducted to: (1) Define and predict the vibrational and chemical nonequilibrium characteristics of hypervelocity flows developed in a contoured nozzle. (2) Evaluate and compute the effects of real-gas chemistry on the characteristics and properties of base flows, interaction regions resulting from shock wave/boundary layer interaction and shock/shock interaction over simple model configurations, and indented nose shapes. (3) Study the characteristics of high-temperature regions of turbulent mixing and combustion associated with scramjet operations at Mach 12. The report is divided into four sections, each of which covers separate but inter-related experimental and theoretical programs that were conducted during the present contract.
Book Synopsis Experiments in Numerical Studies of Low Density and Real Gas Effects on Regions of Shock Wave/boundary Layer Interaction in Hypervelocity Flows by : Michael S. Holden
Download or read book Experiments in Numerical Studies of Low Density and Real Gas Effects on Regions of Shock Wave/boundary Layer Interaction in Hypervelocity Flows written by Michael S. Holden and published by . This book was released on 2006 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experiments with extensive numerical simulations were conducted examining effects of low density flows and real gas effects on aerothermal characteristics of flows in hypervelocity facilities and in simple and complex flowfields in hypervelocity flows. These studies demonstrated that in the absence of real gas effects the DSMC and Navier-Stokes solutions accounting for slip effects were in excellent agreement with measurements. An extensive series of calibration and validation studies were done defining the free stream flows in the LENS I and X tunnels for low density and high enthalpy flows at velocities up to 16,000 ft/s. Measurements on double cone configuration showed that above 13,000 ft/s the interaction regions differed significantly in nitrogen and air flows; while the computations agreed with the measurements in nitrogen, they differed significantly in the size and properties of interaction regions in air. With the shuttle configuration, we demonstrated that real gas effects decrease the size of a separated interaction region over the flap, reduce the pressure over the adjacent curved surfaces, and reduce Reynolds number for onset of boundary layer transition.
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.
Book Synopsis Handbook of Shock Waves, Three Volume Set by : Gabi Ben-Dor
Download or read book Handbook of Shock Waves, Three Volume Set written by Gabi Ben-Dor and published by Elsevier. This book was released on 2000-10-18 with total page 2188 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Handbook of Shock Waves contains a comprehensive, structured coverage of research topics related to shock wave phenomena including shock waves in gases, liquids, solids, and space. Shock waves represent an extremely important physical phenomena which appears to be of special practical importance in three major fields: compressible flow (aerodynamics), materials science, and astrophysics. Shock waves comprise a phenomenon that occurs when pressure builds to force a reaction, i.e. sonic boom that occurs when a jet breaks the speed of sound.This Handbook contains experimental, theoretical, and numerical results which never before appeared under one cover; the first handbook of its kind.The Handbook of Shock Waves is intended for researchers and engineers active in shock wave related fields. Additionally, R&D establishments, applied science & research laboratories and scientific and engineering libraries both in universities and government institutions. As well as, undergraduate and graduate students in fluid mechanics, gas dynamics, and physics. Key Features* Ben-Dor is known as one of the founders of the field of shock waves* Covers a broad spectrum of shock wave research topics* Provides a comprehensive description of various shock wave related subjects* First handbook ever to include under one separate cover: experimental, theoretical, and numerical results
Book Synopsis Computational Studies of Hypersonic High Enthalpy Separated Flows by : Deepak Narayan Ramanath
Download or read book Computational Studies of Hypersonic High Enthalpy Separated Flows written by Deepak Narayan Ramanath and published by . This book was released on 2011 with total page 380 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Similarity Studies for Dissociating Gases in Hypersonic, Low Density Flow by : K. Pearce
Download or read book Similarity Studies for Dissociating Gases in Hypersonic, Low Density Flow written by K. Pearce and published by . This book was released on 1960 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
