Investigations on supersonic combustion in a combustion-driven shock tunnel

Ratan, J and Jagadeesh, G (2012) Investigations on supersonic combustion in a combustion-driven shock tunnel. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 226 (9). pp. 1183-1191.

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his 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° wedge attached to the upstream end of the bottom plate. Gaseous hydrogen is injected at an angle of 45° 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: Article
Uncontrolled Keywords: Supersonic combustion;Shock tunnel;Combustion driver;Hydrogen injection;Gas dynamics
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Propulsion and Power
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Ms. Alphones Mary
Date Deposited: 30 Apr 2013 10:37
Last Modified: 30 Apr 2013 10:37

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