Characterization of a Kerosene-derived Rocket Fuel

سال انتشار: 1386
نوع سند: مقاله کنفرانسی
زبان: انگلیسی
مشاهده: 1,614

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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.

نویسندگان

Reza Ghiai

Iranian Aerospace Organization, Tehran, Iran

Davood Heydari

Iranian Aerospace Organization, Tehran, Iran