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Numirecal simulation of spray evaporation during hybrid rocket engine ignition phase / Mohamed Elshafey Abdallah Awad ; Supervised Samir Abohadima , Farouk Owis , Amr Gamal Gauilly

By: Contributor(s): Material type: TextTextLanguage: English Publication details: Cairo : Mohamed Elshafey Abdallah Awad , 2015Description: 66 P. : charts ; 30cmOther title:
  • المحاكاة العددية لتبخر الرذاذ أثناء اشعال محرك صاروخى مهجن [Added title page title]
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  • Issued also as CD
Dissertation note: Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Mathematics and Physics Summary: 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
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Item type Current library Home library Call number Copy number Status Date due Barcode
Thesis Thesis قاعة الرسائل الجامعية - الدور الاول المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.10.M.Sc.2015.Mo.N (Browse shelf(Opens below)) Not for loan 01010110068107000
CD - Rom CD - Rom مخـــزن الرســائل الجـــامعية - البدروم المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.10.M.Sc.2015.Mo.N (Browse shelf(Opens below)) 68107.CD Not for loan 01020110068107000

Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Mathematics and Physics

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

Issued also as CD

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