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Book The Trend in Engineering at the University of Washington

Download or read book The Trend in Engineering at the University of Washington written by and published by . This book was released on 1959 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Experimental Investigation of the Tailored interface Mode of Operation of the University of Washington Hypersonic Shock Tunnel

Download or read book Experimental Investigation of the Tailored interface Mode of Operation of the University of Washington Hypersonic Shock Tunnel written by Raymond Leroy Enlow and published by . This book was released on 1965 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Masters Theses and Doctoral Dissertations in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States

Download or read book Masters Theses and Doctoral Dissertations in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States written by and published by . This book was released on 1959 with total page 458 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Design of a Hypersonic Shock Tunnel

Download or read book Design of a Hypersonic Shock Tunnel written by Derrill Gene Whitten and published by . This book was released on 1958 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Flow Phenomena in Starting a Hypersonic Shock Tunnel

Download or read book Flow Phenomena in Starting a Hypersonic Shock Tunnel written by Herbert S. Glick and published by . This book was released on 1955 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book The Instrumentation and Calibration of the McGill Hypersonic Shock Tunnel

Download or read book The Instrumentation and Calibration of the McGill Hypersonic Shock Tunnel written by Thomas Kendrick Morton and published by . This book was released on 1964 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt: "This report describes the instrumentation of the recently completed Hypersonic shock tunnel at McGill University. Also included are the results of preliminary testing and calibration carried out on the combustion driver section, the shock tube, and the complete tunnel. The loading system by which the driver gases are metered into the combustion chamber is described, as well as the electrical system used to ignite the mixture. A description of the ionization gages used to measure incident shock velocity, along with the piezo-electric pressure transducers for measuring pressure behind the incident and reflected shocks in the tube, and the stagnation pressure in the test section is also given. The high pressure resulting from the combustion of a stoichiometric mixture of oxygen and hydrogen, diluted with 76 or 80% helium, is used to break a steel diaphragm and compress the test gas by a reflected shock process. Combustion tests produced peak pressures approximately 25% below those predicted by constant volume combustion theory. In the shock tube, incident shock Mach numbers up to 6.69 were produced in air at a pressure of one atmosphere, giving rise to pressures behind the reflected shock of up to 6,500 psi. However, due to attenuation in the tube, these values were about 30% below the results expected from theoretical considerations based on no losses. [...]" --

Book Design and Construction of a Hypersonic Shock Tunnel

Download or read book Design and Construction of a Hypersonic Shock Tunnel written by Nasim Farrukh Amin and published by . This book was released on 1964 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt: "A combustion driven hypersonic shock tunnel has been designed and constructed primarily for the simulation of flows around hypersonic ramjets. This report describes the design and construction of the shock tunnel and discusses its hypersonic simulation capabilities. The construction of the shock tunnel has now been completed and it is ready for instrumentation and calibration. The driving gas is a combustible mixture of stoichiometric hydrogen and oxygen diluted with 60 to 75% helium to avoid detonation. The maximum mixture loading pressure is 2000 psi. The driven gas is air, usually at room temperature and pressure. Successful evacuation of the test section to 5 microns of mercury has been achieved. The shock tunnel has been designed to produce air at minimum stagnation temperature and pressure of 4200°R and 2300 psi respectively and 0 maximum stagnation temperature and pressure of 14300°R and 20,000 psi respectively1 at the nozzle entrance. Air at these stagnation conditions, when expanded in the test section, will completely simulate free flight conditions (i.e., pressure, temperature, unit Reynold's number, Mach number, etc.) in and around a hypersonic ramjet flying over an altitude range of 90,000 ft to 250,000 ft and a corresponding Mach number range of 7.5 to 18.5. Preliminary tests have been successful and have indicated that (a) the recoil mechanism is capable of absorbing the shock forces, (b) the gun barrels, joined end to end, produce a well aligned, rigid and strong driven section and (c) the actual recoil stroke will probably be considerably less than the initially assumed value of 4"." --