Calculation of the limiting characteristics of nozzle electrification in kerosene + liquid oxygen postcombustion flow
Автор: Onufriev V.V., Kramarenko R.M.
Журнал: Космическая техника и технологии @ktt-energia
Рубрика: Тепловые, электроракетные двигатели и энергоустановки летательных аппаратов
Статья в выпуске: 2 (45), 2024 года.
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The study of electrophysical characteristics of a high-enthalpy supersonic postcombustion flow is an urgent issue. The paper discusses calculation of electrification of the nozzle wall of the liquid-propellant rocket engine in interaction with the supersonic flow of «kerosene + liquid oxygen» postcombustion products. A computational study of the characteristics of the supersonic flow in liquid-propellant rocket engine nozzle exit was carried out, distribution of the electric potential in the nozzle wall region was obtained.
Liquid-propellant rocket engine, discharge rate, temperature, combustion products, electrification of the nozzle wall, ambipolar potential
Короткий адрес: https://sciup.org/143183275
IDR: 143183275
