Abstract
The structure of the disturbed area near the internal surface of the nozzle of a liquid-propellant rocket engine (LPRE) and also the distribution of the electrical and physical parameters in the flux of dense weakly ionized plasma are examined by means of mathematical simulation. The results of probe measurements of charged particle concentration in combustion products in the exhaust from the nozzle of a liquid-propellant rocket engine under real conditions at the moment of rocket lift-off from the launching site are presented.
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