High-enthalpy Characterization of the UTA Hypersonic Shock Tunnel PDF Download
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Author: Raheem Temitope Bello
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
In hypersonic wind tunnel testing, matching the flow enthalpy conditions for the hypersonic air-breathing corridor is of great importance in order to assure the validity of experimental results. The flow enthalpy of the UTA hypersonic shock tunnel is increased by a shock-induced detonation driver. The detonation mixture consist of hydrogen and oxygen in stoichiometric quantities (2H2+O2 --> 2H2O). Experimental variations of pressure and the volume of the detonation section were performed to characterize the enthalpy limits, and overall performance of the UTA hypersonic shock tunnel. The UTA HST test section was operated at a nominal Mach number of 10. Force balance experiments were performed in the test section during the high enthalpy characterization. Enthalpy measurements were also performed using a type K thermocouple placed in a Fay-Riddell probe within the test section. High enthalpy flows with maximum total temperature of 4393 K, maximum total pressure of 373 atm, and maximum total enthalpy of 5.1 MJ/kg were achieved in the driven section, with Mach numbers of 8.75 0.25 measured in the test section.
Author: Raheem Temitope Bello
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
In hypersonic wind tunnel testing, matching the flow enthalpy conditions for the hypersonic air-breathing corridor is of great importance in order to assure the validity of experimental results. The flow enthalpy of the UTA hypersonic shock tunnel is increased by a shock-induced detonation driver. The detonation mixture consist of hydrogen and oxygen in stoichiometric quantities (2H2+O2 --> 2H2O). Experimental variations of pressure and the volume of the detonation section were performed to characterize the enthalpy limits, and overall performance of the UTA hypersonic shock tunnel. The UTA HST test section was operated at a nominal Mach number of 10. Force balance experiments were performed in the test section during the high enthalpy characterization. Enthalpy measurements were also performed using a type K thermocouple placed in a Fay-Riddell probe within the test section. High enthalpy flows with maximum total temperature of 4393 K, maximum total pressure of 373 atm, and maximum total enthalpy of 5.1 MJ/kg were achieved in the driven section, with Mach numbers of 8.75 0.25 measured in the test section.
Author: Derek Glenn Leamon
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Characterization of a hypersonic shock tunnel was performed under low enthalpy conditions. A rake was designed and fabricated to measure pitot pressure and heat flux at three axial locations in the test section. Pitot pressures at three locations provided an indication of the inviscid core. Thin film RTD sensors with a fast response time were fabricated to measure the heat flux under these low enthalpy conditions. The Cook-Felderman algorithm was used to estimate the heat flux from the temperature history. Results for the first millisecond of test time showed a probe tip surface temperature increase of 15-20 K and a calculated heat flux in the inviscid core of 9.93 ± 0.56 W/cm2.
Author: Riccardo Bonazza
Publisher: Springer
ISBN: 3319168355
Category : Science
Languages : en
Pages : 832
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Book Description
This proceedings present the results of the 29th International Symposium on Shock Waves (ISSW29) which was held in Madison, Wisconsin, U.S.A., from July 14 to July 19, 2013. It was organized by the Wisconsin Shock Tube Laboratory, which is part of the College of Engineering of the University of Wisconsin-Madison. The ISSW29 focused on the following areas: Blast Waves, Chemically Reactive Flows, Detonation and Combustion, Facilities, Flow Visualization, Hypersonic Flow, Ignition, Impact and Compaction, Industrial Applications, Magnetohydrodynamics, Medical and Biological Applications, Nozzle Flow, Numerical Methods, Plasmas, Propulsion, Richtmyer-Meshkov Instability, Shock-Boundary Layer Interaction, Shock Propagation and Reflection, Shock Vortex Interaction, Shock Waves in Condensed Matter, Shock Waves in Multiphase Flow, as well as Shock Waves in Rarefield Flow. The two Volumes contain the papers presented at the symposium and serve as a reference for the participants of the ISSW 29 and individuals interested in these fields.
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: H. Groenig
Publisher:
ISBN:
Category :
Languages : en
Pages : 87
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Author: W. S. Stuessy
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Author: Cornell Aeronautical Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 84
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Author: Katsuhiro Itoh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Frank K. Lu
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN:
Category : Computers
Languages : en
Pages : 696
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Book Description
With the technical challenges that simulations of Mach 5-plus speeds pose for wind tunnel ground testing facilities, such testing has been characterized as "the art of partial simulation." Lu (mechanical and aerospace engineering, U. of Texas at Arlington) and Marren (Arnold Engineering Development Center, White Oak, MD) introduce 22 contributed chapters expanding the knowledge base on developments in hypersonic facilities in the past decade by focusing on testing principles; specific types of facilities (e.g., NASA's HYPULSE, LENS hypervelocity tunnels, and the U-12 large shock tube); and innovations including new instrumentation capabilities, advances in material sciences, and increasing international cooperation. Readers are referred elsewhere for treatment of perfect gas wind tunnels. Annotation copyrighted by Book News, Inc., Portland, OR
Author: Frank K. Lu
Publisher: AIAA
ISBN: 9781600864483
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 694
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