Based on the detailed chemical reaction mechanism

the flow and radiation of the plume were studied by the method of computational fluid dynamics (CFD) + line-by-line integration and light of sight method. The effects of different chemical reaction mechanisms on flow and radiation were compared and analyzed. The validity of the model was verified by optical measurement data. On this basis

the influence of rocket exit parameters on plume flow and radiation was analyzed in detail. The results showed that: the temperature of the nozzle exit had little effect on the structure of the flow field

but had a significant effect on the afterburning; the increase of pressure at the nozzle exit had an effect on the wave structure of the Maher disk

but had little effect on the afterburning; the infrared radiation intensity of the plume increased with the increase of the temperature and pressure of the nozzle exit

and the infrared radiation intensity was positively related to the thrust of the engine.