Numerical Study of Unsteady Shock Waves in Hypersonic Nozzle Flows PDF Download
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Author: Munetsugu Kaneko
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Munetsugu Kaneko
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Goetz H. Klopfer
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 16
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792706677
Category :
Languages : en
Pages : 26
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Book Description
A complex two-dimensional, unsteady, viscous hypersonic shock wave interaction is numerically simulated by a high-resolution, second-order fully implicit shock-capturing scheme. The physical model consists of a nonstationary oblique shock impinging on the bow shock of a blunt body. Studies indicated that the unsteady flow patterns are slightly different from their steady counterparts. However, for the sample cases investigated the peak surface pressures for the unsteady flows seem to occur at very different impingement locations than for the steady flow cases. Klopfer, G. H. and Yee, H. C. and Kutler, P. Ames Research Center NASA-TM-100096, A-88147, NAS 1.15:100096 ...
Author: Robert E Dillon (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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A numerical study was made of the test time in a hypersonic shock tunnel for Mach 10 flow. Harten's total variation diminishing (TVD) scheme was used to simulate the entire shock tunnel operation from diaphragm rupture to disruption of the flow in the nozzle. The code was able to model the main features of unsteady flow in a shock tube to include the shock wave and contact surface intersections. Results were obtained that predict the steady flow duration time for stagnation temperatures of 1200F, 2700F, and 6900F. Both air and helium were used as driver gases with air as the test gas.
Author: Raymond Brun
Publisher: Springer Science & Business Media
ISBN: 3642788297
Category : Science
Languages : en
Pages : 497
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Book Description
Recently, there have been significant advances in the fields of high-enthalpy hypersonic flows, high-temperature gas physics, and chemistry shock propagation in various media, industrial and medical applications of shock waves, and shock-tube technology. This series contains all the papers and lectures of the 19th International Symposium on Shock Waves held in Marseille in 1993. They are published in four topical volumes, each containing papers on related topics, and preceded by an overview written by a leading international expert. The volumes may be purchased independently.
Author: Charles Edward Smith
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 114
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Author: Gabi Ben-Dor
Publisher: Springer
ISBN: 331946213X
Category : Technology & Engineering
Languages : en
Pages : 746
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Book Description
These proceedings collect the papers presented at the 30th International Symposium on Shock Waves (ISSW30), which was held in Tel-Aviv Israel from July 19 to July 24, 2015. The Symposium was organized by Ortra Ltd. The ISSW30 focused on the state of knowledge of the following areas: Nozzle Flow, Supersonic and Hypersonic Flows with Shocks, Supersonic Jets, Chemical Kinetics, Chemical Reacting Flows, Detonation, Combustion, Ignition, Shock Wave Reflection and Interaction, Shock Wave Interaction with Obstacles, Shock Wave Interaction with Porous Media, Shock Wave Interaction with Granular Media, Shock Wave Interaction with Dusty Media, Plasma, Magnetohyrdrodynamics, Re-entry to Earth Atmosphere, Shock Waves in Rarefied Gases, Shock Waves in Condensed Matter (Solids and Liquids), Shock Waves in Dense Gases, Shock Wave Focusing, Richtmyer-Meshkov Instability, Shock Boundary Layer Interaction, Multiphase Flow, Blast Waves, Facilities, Flow Visualization, and Numerical Methods. The two volumes serve as a reference for the participants of the ISSW30 and anyone interested in these fields.
Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
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.
Author: Shaye Yungster
Publisher:
ISBN:
Category : Chemical reaction, Conditions and laws of
Languages : en
Pages : 24
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Author: Harold Mirels
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
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Self-similar flows with volumetric mass, momentum, and energy addition are investigated. Unsteady flows bounded by shock waves and equivalent steady hypersonic flows over slender bodies are considered, and the form of the shock shape and of the volumetric sources for self-similar motion are noted. For unsteady flows, it is found that the shock shape mu t have the form R sub O=ct to the m power (where R sub O = shock ordinate, t = time) and that the mass, momentum, and energ sources must be expressible in the fom of a funtion of r/R sub O times t to the -1 power, t to the m-2 power, and t to the 2m-3 power, respectively (where r is the lateral ordinate). If the sources introduce only sll perturbations in an otherwise self-similar flow, solutions can be obtained for sources expressible as a function of r/R sub O times t to arbitrary constant exponents. Thus, the small perturbation case is less restrictive with regard to the functional form of the sources. For equivalent steady hypersonic flows, the streamwise distance, x, replaces t in the above expressions. Numerical perturbation solutions are obtained for the effect of a uniform transverse magnetic field on piston-driven flows and blast waves. The firstorder effect of body-thickness raio on the hypersonic flow (in the limit of infinite Mach number) over slender power law bodies is aso reated. (Author).
