To study the impact effect of liquid rocket motor exhaust plume on launching platform

a mathematical calculation model of exhaust plume impact on launching platform for liquid rocket motor was built. For the impact effect of LOX (liquid oxygen)/ kerosene exhaust plume on the launching platform

the influences of the propellant flux and afterburning on the impact effect from the nozzle exit to the platform in two different cases of 3m and 5m were studied

the differences and the reasons for the differences were also analyzed. Results show that

with the increase of the propellant flux

the distance of shock wave expansion and compression of the free jet region and the area of the wall-jet region increased. Afterburning can not only change the structure of the free jet region and the stagnation zone

but also increase the temperature and the area of the wall-jet region. Afterburning and propellant flux influence the impact effect by generating influence on the structure of the exhaust plume

and the impact effect is related to the distance from the nozzle exit to launching platform.