Abstract
Experimental and numerical studies on the interaction between combustion of a hydrogen jet and an incident shock wave were performed. When the incident shock wave was introduced upstream of the injection slot, the boundary-layer separation region was expanded extensively. The penetration height, defined as the height of the Mach disk, with the incident shock wave was less than that without the incident shock wave. Combustion was confirmed when the incident shock wave was introduced downstream of the fuel injection slot. However, combustion was not confirmed with the incident shock wave upstream of fuel injection slot. The mechanism of these phenomena was examined based on the numerical simulation results in terms of the characteristic residence time in the separation region near the fuel injection slot.
| Original language | English |
|---|---|
| Pages (from-to) | 170-175 |
| Number of pages | 6 |
| Journal | Transactions of the Japan Society for Aeronautical and Space Sciences |
| Volume | 51 |
| Issue number | 173 |
| DOIs | |
| Publication status | Published - 2008 |
Keywords
- Combustion
- Compressible flow
- Shock waves
ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science