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Titlebook: New Trends in Instrumentation for Hypersonic Research; A. Boutier Book 1993 Springer Science+Business Media Dordrecht 1993 CFD.Schlieren p

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書(shū)目名稱New Trends in Instrumentation for Hypersonic Research
編輯A. Boutier
視頻videohttp://file.papertrans.cn/666/665962/665962.mp4
叢書(shū)名稱NATO Science Series E:
圖書(shū)封面Titlebook: New Trends in Instrumentation for Hypersonic Research; A. Boutier Book 1993 Springer Science+Business Media Dordrecht 1993 CFD.Schlieren p
描述Because of the growing interest in hypersonic flows, the AGARD Fluid Dynamics Panel initiated a sub-working group on instrumentation for hypersonics in 1989. This sub-group, chaired by J. WENDT (VKI -Belgium), was composed of: A. BOUTIER (ONERA -France), K. BUTEFISCH (DLR -Germany), R. CATTOLICA (SANDIA Lab. -USA), V. CLINE (AEDC -USA), A. GIRARD (ONERA -France), R. McKENZIE (NASA Ames -USA), S. OCHELTREE (NASA Langley -USA) and G. SMEETS (ISL -Franco-German Inst.). As a result of several meetings, the idea came to organize this workshop, 27th April - 1st May 1992, on "New Trends in Instrumentation for Hypersonic Research", at Le Fauga-Mauzac ONERA center, in France, where the new hot-shot arc-heated facility F4, as well as a new conference building, were recently completed. This workshop has been organized in close connection with the AGARD FDP Symposium to be held in Torino 4 - 8 May 1992 on "Theoretical and Experimental Methods in Hypersonic Flows": the main conclusions and ideas expressed by the papers and during the discussions of this workshop are reported in session 7 and have been presented in Torino in a special Instrumentation session. As chairman of this workshop, I expr
出版日期Book 1993
關(guān)鍵詞CFD; Schlieren photography; aerodynamics; dynamics; electron; flow; flows; fluorescence; interferometry; lase
版次1
doihttps://doi.org/10.1007/978-94-011-1828-6
isbn_softcover978-94-010-4807-1
isbn_ebook978-94-011-1828-6Series ISSN 0168-132X
issn_series 0168-132X
copyrightSpringer Science+Business Media Dordrecht 1993
The information of publication is updating

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發(fā)表于 2025-3-21 21:30:57 | 只看該作者
Hot Experimental Technique: a New Requirement of Aerothermodynamicspical measurement problems, is pro-posed. Details of the technique, regarding the tunnel type, model and measurement techniques are discussed. A stepwise approach to the involved problems is suggested.
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5#
發(fā)表于 2025-3-22 11:37:31 | 只看該作者
Laser-Based Diagnostics for Hypersonic Flows shock tunnel. These methods have unique capabilities for nonintrusive measurements of flowfield properties such as temperature, species concentration, velocity, density and pressure, as well as quantities derived from these properties such as mass flux (product of velocity and mass density).
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發(fā)表于 2025-3-22 15:39:12 | 只看該作者
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發(fā)表于 2025-3-22 19:13:48 | 只看該作者
Requirements for Facilities and Measurement Techniques to Support CFD Development for Hypersonic Airt for the design of hypersonic aircraft. Illustrations are given of recent success in combining experimental and direct numerical simulation in CFD model development and validation for hypersonic perfect gas flows.
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發(fā)表于 2025-3-22 22:34:09 | 只看該作者
Hermes Measurement Needs in Hot Facilitiess (very short time duration, high level of temperature, wide range in level of pressure…). They are required for post processing data analysis and validation of numerical codes. The paper describes the different parameters to be measured.
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發(fā)表于 2025-3-23 03:49:15 | 只看該作者
Computation and Experimentation of Free Piston Shock Tunnels — Example of the Marseille Facilityigh enthalpy flows characteristic of the reentry phase of the Hermes european shuttle. Preliminary results of pressure measurements in the compression chamber are also presented and compared with computational data.
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發(fā)表于 2025-3-23 08:00:17 | 只看該作者
Ground Test Facilities and Instrumentation for Aerothermal and Aero-Optical Studies of Hypersonic Ine and flowfield instrumentation that will be used to determine the aerothermal characteristics of the flowfield over the hypersonic vehicle is described. Finally we discuss the aero-optic instrumentation which is used to evaluate the optical degradation through the shock layer surrounding the vehicle.
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