Numerical-Study of Large-Liquid Rocket Plume-Flow-Field

Abstract

Aiming at the complexity of plume field structure caused by plume collision in the rising section of multi-nozzle parallel rocket, this paper establishes an analytical model of the rising section of a nine-nozzle configuration rocket. The plume field phenomenon is studied at different heights through numerical simulation. The reliability of the numerical method is verified based on the comparison of simulation and wind tunnel test data. The analytical results. Show that violent collision occurs between the jets in the ascent section of the multi-nozzles rocket, and many phenomena such as circulating vortex, gas reflux, reflux back splash and so on occur at different altitudes. When the altitude is less than 25km, gas reflux and circulation vortex appear in the rocket base. With the increasing of altitude, the jet collision impacts the base. After the altitude reaches 45km, back splash appears in some areas of the rocket base. There is an obvious flow diversion phenomenon on the side wall surface. The higher the altitude, the greater the expansion angle of the jet after the gas exits the nozzle.