بررسی خواص ترموفیزیکی سوخت کروسینی حاوی نانولوله کربنی برای خنک کاری محفظه احتراق راکت

The engine cooling in first stage of satellite carrier rocket via kerosene fuel leads to increase the missile range. For increasing the heat transfer coefficient of the fuel, addition of nanoparticle is a preferred method. At constant velocity of nanofuel through the fuel flow passage in combustion chamber, evaluation of the coefficient depends on assessment of the effective parameters. These parameters are: density, specific heat capacity, thermal conductivity and viscosity of the nanofuel. In this article, the kerosene nanofuel was prepared by addition of carbon nanotube with surfactant oleyl amine to the kerosene fuel. Then, effect of volume fraction of carbon nanotube on the thermophysical properties of the fuel was studied in the range of 0 to 0.08 at 30 oC. Mouromtseff number (as a thermal performance index of a liquid fuel) was obtained more than 1 for the kerosene nanofuel with respect to base fuel, indicating the increasing the heat transfer coefficient for the kerosene nanofuel.