| Citation: | ZHOU Zhitan, LI Yiqing, JIANG Ping, et al. Effect of secondary combustion on the multi-nozzle rocket base thermal environment[J]. Journal of Aerospace Power, 2024, 39（6）：20210694 doi: 10.13224/j.cnki.jasp.20210694
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During rocket launching, the secondary combustions between the fuel-rich exhaust gas and the oxygen of air were made, leading to a temperature rise. Based on three-dimensional compressible Navier-Stokes equation, hybrid RANS/LES turbulence model, DOM model, and finite-rate chemical kinetics, the reaction model of multi-nozzle rocket was established. And the validity of model was verified by comparing with the wind tunnel experimental data. Then, a comparison study between reaction and frozen flows of two-/four-nozzle rockets was developed. The results showed that the secondary combustion mainly occurred in the mixed layer. With the increase of the flight altitudes, the increase of the peak temperature caused by afterburning decreased, while the maximum was 10.16% and the minimum was 0.86%. At the same height, the afterburning effect was strengthened with increasing distance from nozzle exit. Comparing with two-nozzle rocket, the afterburning had less effect on the four-nozzle rocket base thermal environment. In addition, the peak heat flux of the rocket base increased first and then decreased with height.
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