| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 9823147 | Acta Astronautica | 2005 | 6 Pages |
Abstract
An experimental study using reflected-type of shock tunnel has been conducted to investigate the phenomena of supersonic combustion. In the experiment, test air is compressed by reflected shock wave up to stagnation temperature of 2800 K and stagnation pressure of 0.35 MPa. Heated air is used as a reservoir gas of supersonic nozzle. Hydrogen is injected transversely through circular hole into freestream of Mach 2. Flow duration is 300 μs. Schlieren method and CCD UV camera are used to obtain information on the shock structures and the region of combustion. The effects of total pressure of injection gas to the fuel penetration and the region of combustion have been obtained.
Related Topics
Physical Sciences and Engineering
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Aerospace Engineering
Authors
Shigeru Aso, Arif Nur Hakim, Shingo Miyamoto, Kei Inoue, Yasuhiro Tani,