Shock Tube Experiments for the Development of a Hydrogen-fueled Pulse Detonation Engine PDF Download
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Author: J. B. Hinkey
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: J. B. Hinkey
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Zonglin Jiang
Publisher: Springer Science & Business Media
ISBN: 3540270094
Category : Science
Languages : en
Pages : 1346
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The 24th International Symposium on Shock Waves (ISSW24) was held at the Beijing Friendship Hotel during July 11-16, 2004, in Beijing. It was a great pleasure for the Local Organizing Committee to organize the ISSW in China for the first time, because forty-seven years have passed since the First Shock Tube Symposium was held in 1957 at Albuquerque. The ISSW24 had to be postponed for one year because of the SARS outbreak in Beijing shortly before the Symposium was scheduled to be held in 2003, but it has achieved success due to the continuous support and kind understanding from all the delegates. It is very heart-warming to have had such an experience and I am very happy to have served as chairman for the Symposium. I would like to thank all for the contributions and help that they have given us over the past three years, without which we would not have had the Symposium. A total of 460 abstracts were submitted to the ISSW24. Each of the abstracts was evaluated by three members of the Scientific Review Committee and the decision on acceptance wasmade based on the reviewers' reports. 195oral papers,including 9plenary lectures, wereaccepted to be presented in three parallel sessions, and 135poster papers in three dedicated poster sessions. Topics discussed in these papers cover all aspects ofshock wave research.
Author: Robert J. McMillan
Publisher:
ISBN: 9781423519164
Category : Internal combustion engines
Languages : en
Pages : 104
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Shock tubes utilize a difference in pressures between gases separated by a diaphragm to create a shock wave when the diaphragm ruptures. The AFIT 2- inch shock tube was reassembled and tested to ensure proper and safe operation. A high-speed data acquisition system was configured to take data at 2 MS/s. This research showed that the Mach number of the shock waves produced in this shQCk tube fall within 7% of theoretical values at speeds under Mach 3 and within 9% at higher speeds. The peak velocity of each shock wave was shown to occur at approximately 3 meters from the diaphragm. The second portion of the research focused on the testing of sensors used to evaluate the performance of the pulse detonation engine (PDE) for research and developmental purposes. Two alternatives were developed to standard sensors to withstand the heat of the engine: coat the sensors with an insulating, 0.6 mm thick silicone that protects it from the heat and use spark plugs as ion sensors to detect the ions in the combustion inside the PDE tubes. This researched proved that no degradation in response time, rise time, or sensitivity results from coating the pressure transducers with silicone. The research also found that the ion sensors are unable to consistently detect ions created by a Mach 8 shock wave through air.
Author: S. N. B. Murthy
Publisher: AIAA
ISBN: 9781600864216
Category : High-speed aeronautics
Languages : en
Pages : 716
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Annotation There have been impressive achievements in the last few years in the technologies associated with turboramjets and other combined cycle engines. These technologies, including their thermal management and integration with the vehicle, are the principal concerns of this volume. Drawing on the expertise of international engineers and researchers in the field of high-speed vehicle propulsion systems, these articles, written by experts from the United States, Russia, Germany, Japan, Belgium, and Israel, highlight developments in the industry.
Author: R. J. Litchford
Publisher:
ISBN:
Category : Detonation waves
Languages : en
Pages : 52
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 658
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
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Author: Jim J. Jones
Publisher:
ISBN:
Category : Helium
Languages : en
Pages : 716
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An experimental investigation has been made of the attenuation of strong shock waves in air in a shock tube. Time-history measurements were made of the static pressure at several stations in the wall of the tube. The internal diameter of the tube is 3.75 inches. shock-wave-velocity data were taken for a distance along the tube of about 120 feet.
Author: American Institute of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1252
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Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 640
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