Characterization of a Kerosene-derived Rocket Fuel
محل انتشار: پنجمین کنگره بین المللی مهندسی شیمی
سال انتشار: 1386
نوع سند: مقاله کنفرانسی
زبان: انگلیسی
مشاهده: 1,670
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شناسه ملی سند علمی:
ICHEC05_417
تاریخ نمایه سازی: 7 بهمن 1386
چکیده مقاله:
One-formula surrogate fuel formulation is developed to support the design of injectors and thrust chambers of kerosene-fueled rocket engines. This surrogate fuel model depicts a fuel blend that properly represents the general physical and chemical properties of rocket fuel (RF). The accompanying gaseous-phase thermodynamics of the surrogate fuel is anchored with the heat of formation of RF and verified by comparing a series of rocket thrust chamber calculations. The final thermophysics formulations are incorporated with a computational model for prediction of the combustor efficiency of a bi-propellant combustor. The model predictions agreed reasonably well with those of the tests.
کلیدواژه ها:
نویسندگان
Reza Ghiai
Iranian Aerospace Organization, Tehran, Iran
Davood Heydari
Iranian Aerospace Organization, Tehran, Iran