supersonic combustion enhancement by shock wave impingement for scram-jet engine
- Paper number
IAC-08.C4.5.9
- Author
Mr. Arif Nur Hakim, Indonesian National Institute of Aeronautics and Space-LAPAN, Indonesia
- Coauthor
Prof. Shigeru Aso, Kyushu University, Japan
- Coauthor
Dr. Yasuhiro Tani, Kyushu University, Japan
- Year
2008
- Abstract
An experimental study of supersonic combustion enhancement by shock wave impingement has been conducted in supersonic high temperature air flow generated by reflected type shock tunnel. The air flow has stagnation temperature of 2800 K and stagnation pressure of 0.35 MPa in duration of around 300 microseconds. Hydrogen and Helium are injected transversely into the Mach 2 air flow through 2mm-diameter circular sonic nozzle. Three different ramps, which have wedge angles of 5°, 10° and 15°, are mounted on the opposite wall of injection hole to generate shock waves directed to mixing plume. Schlieren method is used to visualize flow pattern and shock structures and the UV-CCD camera is used to observe region of combustion by catching the self luminescence of OH radicals produced in combustion process. The combination of Schlieren images and UV images shows the shock structure in the flow field and its effect to the supersonic combustion. It is found that shock wave impingement enhances the combustion and separated region formed by stronger shock impingement, could work as flame-holder.
- Abstract document
- Manuscript document
IAC-08.C4.5.9.pdf (🔒 authorized access only).
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