고도와 후연소를 고려한 고체 로켓모터의 배기 플룸 열유동장 해석에 관한 연구

For the prediction of the rocket base heating and infrared signature from the exhaust plume of the solid rocket motor, it is highly needed to analyze the thermal flow field of the exhaust plume. In this work, therefore, the exhaust plume of the solid rocket motor was analyzed using the commercial CFD code, Fluent with different operating and environmental situations. Firstly, basic conditions of altitude was incorporated with afterburning of the incompletely combusted fuel components in the combustion chamber with detailed reaction chemistry. Also, the behavior of the particles binding the solid propellant was analyzed using the DPM. As altitude increases, due to the atmospheric pressure change and the under-expansion effect it can be found that the plume size is increased. Also, it was confirmed that the smaller particles are distributed more widely in the radial direction and the larger particles are concentrated in the center of the plume due to the relatively large inertia, and a local temperature rise is occurred in the mixing layer of the exhaust plume due to afterburning and increased the size of the plume. Finally, it is noted that OH radical, a chemical species that did not exist at the nozzle inlet, was generated by chemical reaction.