TY  - BOOK
AU  - Mohamed Elshafey Abdallah Awad
AU  - Amr Gamal Gauilly , 
AU  - Farouk Owis , 
AU  - Samir Abohadima , 
TI  - Numirecal simulation of spray evaporation during hybrid rocket engine ignition phase / 
PY  - 2015///
CY  - Cairo : 
PB  - Mohamed Elshafey Abdallah Awad , 
KW  - Hybrid Engine
KW  - Ignition
KW  - Two phase flow
N1  - Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Mathematics and Physics; Issued also as CD
N2  - 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
ER  -