Abstract
Experimental study of the plasma igniter was conducted in non-heated high-speed airstream. The effects of the Mach number and the stagnation pressure of the airstream as well as the hydrogen fraction in the H2/N2 feedstock of the torch were investigated. In the higher Mach number airstream, more input power to the torch was required to ignite hydrogen fuel. The stagnation pressure of the airstream had complicated effects relating chemistry and aerodynamics. Improvement of ignition performance due to the increased hydrogen fraction in the feedstock was well correlated with the sum of the electric input energy and the heat of combustion of the hydrogen fed as the feedstock of the torch.
| Original language | English |
|---|---|
| Publication status | Published - 2001 Dec 1 |
| Event | 39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV, United States Duration: 2001 Jan 8 → 2001 Jan 11 |
Other
| Other | 39th Aerospace Sciences Meeting and Exhibit 2001 |
|---|---|
| Country | United States |
| City | Reno, NV |
| Period | 01/1/8 → 01/1/11 |
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
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Cite this
Masuya, G., Takita, K., Takahashi, K., Takatori, F., & Ohzeki, H. (2001). Effect of airstream mach number on H2/N2 plasma igniter. Paper presented at 39th Aerospace Sciences Meeting and Exhibit 2001, Reno, NV, United States.