Development of a short duration hypersonic test facility at Universiti Tenaga Nasional

Al-Falahi, Amir and Yusoff, Mohd. Zamri bin and Yusaf, Talal (2008) Development of a short duration hypersonic test facility at Universiti Tenaga Nasional. Institution of Engineers, Malaysia. Journal, 69 (1). pp. 19-25. ISSN 0126-513X

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Abstract

[Abstract]: This paper describes the development of a short duration hypersonic test facility at the College of Engineering, Universiti Tenaga Nasional (UNITEN). The facility is the first of its kind in Malaysia. The facility will allow various researches to be done in the field of high speed supersonic and hypersonic flows. It is designed so that it can be used as a free piston tunnel, shock tube and shock tunnel. The maximum mach number obtainable depends on the type of the driver and driven gases. It is shown that a mach number of 4 can be achieved if CO2 is used as the driven gas and Helium is used as the driver gas with diaphragm pressure ratio of 74.76. Experimental measurements were performed with the facility working as shock tube. The barrel temperature was measured using in-house developed fast response surface junction E-type thermocouple while the pressure was measured using fast response quartz pressure transducer. The pressure and temperature results clearly show the formation of shock wave and its reflection causing the pressure and temperature to increase rapidly.


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Item Type: Article (Commonwealth Reporting Category C)
Refereed: Yes
Item Status: Live Archive
Depositing User: Dr Talal Yusaf
Faculty / Department / School: Historic - Faculty of Engineering and Surveying - Department of Mechanical and Mechatronic Engineering
Date Deposited: 09 Dec 2008 01:58
Last Modified: 09 Dec 2013 02:45
Uncontrolled Keywords: hypersonic test facility, shock tunnel, shock tube, free-piston tunnel, shock wave
Fields of Research (FOR2008): 09 Engineering > 0915 Interdisciplinary Engineering > 091504 Fluidisation and Fluid Mechanics
09 Engineering > 0901 Aerospace Engineering > 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
URI: http://eprints.usq.edu.au/id/eprint/4643

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