Ratan, J and Jagadeesh, G (2012) Investigations on supersonic combustion in a combustion-driven shock tunnel. In: PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, 226 (G9). pp. 1183-1191.
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This article reports experimental results on supersonic combustion in a new facility. The facility is a combustion-driven shock tunnel, which is cheaper to build than the facilities in which such experiments are carried out conventionally. The observation region is a zone between two parallel flat plates with a 33 degrees wedge attached to the upstream end of the bottom plate. Gaseous hydrogen is injected at an angle of 45 degrees into an oncoming supersonic flow of Mach 2 (approximate) from a port on the bottom plate. The resulting flow field is visualized by a high speed camera in a dark background. Three different test gases, namely nitrogen, air, and oxygen-rich air are used, and the results are compared. A distinct luminosity due to combustion for oxygen-containing test gases is observed. Heat-transfer rates on a probe placed at the downstream end of the observation region and midway between the parallel plates are measured and compared for the three cases. Wall static pressure at 28 mm downstream of the injection port on the bottom plate is also presented.
|Item Type:||Journal Article|
|Additional Information:||Copyright for this article belongs to SAGE PUBLICATIONS LTD, ENGLAND|
|Keywords:||supersonic combustion;shock tunnel;combustion driver;hydrogen injection;gas dynamics|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||27 Nov 2012 10:07|
|Last Modified:||27 Nov 2012 10:07|
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