Interferometric Data for a Shock-wave/boundary-layer Interaction PDF Download
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Author:
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ISBN:
Category :
Languages : en
Pages : 274
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 274
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Author: J.C. Hsu
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Category :
Languages : en
Pages :
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Author: Alfred Curtis Hunting
Publisher:
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Category :
Languages : en
Pages : 282
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Author: Kazuyoshi Takayama
Publisher: Springer
ISBN: 3030194515
Category : Science
Languages : en
Pages : 719
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Book Description
This book presents a wealth of images of shock wave phenomena, gathered by the author over the past 40 years. Shadowgrams and interferograms of basic shock-dynamic topics such as reflection, diffraction, refraction, and focusing of shock waves in gases and liquids are sequentially displayed. Though the images themselves are self-explanatory, brief explanations of the experimental conditions are included, so as to facilitate analysis and numerical reproduction of the image data. In addition, the book presents interferometric observations of underwater shock wave/bubble interactions, and highlights the multifaceted applications of shock wave phenomena to medicine and industry. Given its scope, the book offers a unique resource for students and researchers who are interested in shock wave phenomena. However, the content has also been specifically prepared for the benefit of readers who are interested in gas dynamics and medical applications of shock waves, and are looking for reliable experimental images.
Author: Mark Paul Loomis
Publisher:
ISBN:
Category :
Languages : en
Pages : 266
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Author: Stephen Emil Dunagan
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Category :
Languages : en
Pages : 526
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Category : Aeronautics
Languages : en
Pages : 400
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Author: T. J. Garrison
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Category :
Languages : en
Pages :
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Author:
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Category :
Languages : en
Pages : 152
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This report investigated fundamental aerothermal phenomena in hypersonic flow, with particular emphasis on viscous/inviscid interaction phenomena. The experimental studies were conducted to examine the changes in the structure at the base of a hypersonic turbulent boundary layer as it is subjected to a strong self-induced pressure gradient in regions of shock wave/ boundary layer interaction. The initial phase of the theoretical program was directed toward summarizing existing techniques for obtaining Navier/Stokes solutions for laminar flow over flat plates in hypersonic flow. In the experimental program, surface and flow field measurements were made to examine the detailed flow mechanics associated with turbulent boundary layer separation over a large cone flare model at Mach numbers 11, 13 and 16 and Reynolds numbers up to 100 million. Holography measurements were used to examine the flow field regions of hypersonic shock wave/turbulent boundary layer interaction. In this preliminary investigation of the application of holography in a 96 inch Shock Tunnel, holographic interferograms were obtained for viscous/inviscid interactions at Mach numbers 11 and 13 and Reynolds numbers up to 30 million, nominally. Flow field studies were made for flat plate/wedge, cone/flare and incident shock configurations. The quantitative results presented offer new information as well as a potential to obtain density measurements in other types of hypersonic flow; however, they also reveal important concerns which need to be resolved before the interferometric data can be claimed to give accurate measurements of these flows. Two appendices include an invited review paper on aerothermal problems associated with hypersonic flight.
Author: K. Takayama
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 27
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Book Description
Analyses are made of the mutual interactions between shock structure and the sidewall laminar boundary-layer and their effects on the quasi-steady flat-plate laminar boundary layer in ionizing argon shock-tube flows. The mutual interactions are studied using effective quasi-one-dimensional equations derived from an area-averaged-flow concept in a finite-area shock tube. The effects of mass, momentum and energy non-uniforities and the wall dissipations in the ionization and relaxation regions on the argon shock structure are discussed. The new results obtained for shock structure, shock-tube laminar sidewall and quasi-steady flat-plate boundary-layer flows are compared with dual-wavelength interferometric data obtained from utias 10 cm x 18 cm Hypervelacity Shock Tube.
