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 microseconds. Schlieren method and CCD UV camera is 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 revealed.
| Original language | English |
|---|---|
| Pages | 7166-7171 |
| Number of pages | 6 |
| Publication status | Published - 2004 |
| Event | International Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada Duration: Oct 4 2004 → Oct 8 2004 |
Other
| Other | International Astronautical Federation - 55th International Astronautical Congress 2004 |
|---|---|
| Country/Territory | Canada |
| City | Vancouver |
| Period | 10/4/04 → 10/8/04 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science