الفهرس Only 14 pages are availabe for public view
 |  | from | 87 |  |  |
| | | from | 87 | | |
Abstract
In hybrid rocket engines, the engine performance and combustion stability is highly affected by existence of vapor oxidizer inside the boundary layer of the solid grain. A numerical study of the evaporation process of liquid oxidizer before reaching the solid grain in hybrid rocket engines is carried out. Factors affecting the rate of vaporization are studied, namely: (i) the igniter gases temperature; (ii) the injected liquid propellant velocity; and (iii) the Igniter to liquid propellant mass flow rate ratio. The study reveals that the droplet size and the igniter to liquid propellant mass flow rate ratio have a major impact on the rate of liquid propellant evaporation