Abstract
The mixing fields within a scram-jet combustion chamber are visualized using pressure-sensitive paint (PSP) as an oxygen sensor. The experiments are performed in a small supersonic wind tunnel at the National Aerospace Laboratory - Kakuda Research Center (NAL-KRC). The main stream Mach number is 2.4, and the dynamic pressure ratios between the injected gas and the main stream are 0.3, 0.7, 1.1 and 1.5. Three fuel injection nozzles are used; both oxygen and air are injected from these nozzles. The spread of the injected gas is measured to observe the effects of placing the nozzles in different positions. The results show that the jet has its own independent flow structure, and that little mixing of gases occurs between the flow structures created by each nozzle. When the injection dynamic pressure ratio is increased, the fuel mixing in the vicinity of the wall surface decreases.
Original language | English |
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Publication status | Published - 2002 Dec 1 |
Event | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States Duration: 2002 Jan 14 → 2002 Jan 17 |
Other
Other | 40th AIAA Aerospace Sciences Meeting and Exhibit 2002 |
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Country/Territory | United States |
City | Reno, NV |
Period | 02/1/14 → 02/1/17 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering