Author: Zonglin Jiang
Publisher: Cambridge University Press
ISBN: 1009035673
Category : Technology & Engineering
Languages : en
Pages : 316
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Book Description
Introducing the state-of-the-art of hypervelocity shock tunnels, this complete reference features a variety of drivers and step-by-step introductions to their theories, physics, methods and testing. This book enables researchers and engineers in aerospace to design and improve wind tunnels that simulate flow qualities of real hypersonic flyers.
Author: Zonglin Jiang
Publisher: Cambridge University Press
ISBN: 131651675X
Category : Technology & Engineering
Languages : en
Pages : 315
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Book Description
A comprehensive reference on the basics, physics, design methods, and testing of various state-of-the art hypervelocity shock tunnels.
Author: Bernard E. Cunningham
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 620
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Book Description
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: Canada. Defence Research Board
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
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Book Description
The driver-reservoir method of extending the test time of a tailored hypersonic shock tunnel by using a reservoir and a nozzle (perforated plate) at the upstream end of the driver is treated theoretically. It is shown that the flow following the rupture of the diaphragm is highly complex and contains both steady and unsteady flow regimes. It is also shown that the area ratio of the nozzle separating the driver from the reservoir determines the nature of the wave system produced. For a unique or 'ideal' nozzle area ratio a flow system is produced which contains no downstream running disturbances other than Mach waves. That is, both the head and the tail of the initial rarefaction wave are prevented from interfering with the shock-tunnel reservoir. Consequently, the running time of the shock tunnel can be extended. The ideal area ratios are calculated for a wide range of shock tunnel operating conditions and compared with experimental results. The comparison shows that the ideal nozzle area ratio can be predicted accurately from theory. (Author).
Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 46
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Book Description
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 824
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Book Description
Author: E. E. Edenfield
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 40
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Book Description
Comparison is made of force, pressure, heat-transfer, and shock shape data from tests in the AEDC-VKF hotshot tunnels and in the Cornell Aeronautical Laboratory 48 Inch Shock Tunnel. Several cone models of varying bluntness were tested through an angle-of-attack range of 0 to 40 deg at each facility. Excellent agreement of the hotshot and the shock tunnel data is shown. (Author).
Author: Casimir J. Jachimowski
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 16
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Book Description
