偏二甲肼/四氧化二氮火箭发动机尾焰流场特性三维仿真研究

以偏二甲肼/四氧化二氮（UDMH/NTO）火箭发动机为研究对象，采用κ-ε湍流模型，运用PISO算法分别对发动机内流-场和尾焰流场进行三维仿真。采用相同方法计算液氢/液氧（LH2/LOX）火箭发动机尾焰，仿真结果和试验结果吻合得较好，证明了计算模型的正确性与有效性；同时对比分析了UDMH/NTO发动机与LH2/LOX发动机尾焰流场特性。结果表明，两者具有相似的温度和马赫数变化趋势，但是UDMH/NTO发动机尾焰核心区温度相对较低，而LH2/LOX发动机尾焰将更快衰减至亚声速射流。

Three-dimensional Simulation Study of UDMH/NTO Rocket Engine Plume Flow Field Characteristics

This passage is modeled with UDMH/NTO rocket engine, and use theκ-ε turbulence model, PISO algorithm to simulate the rocket lfow ifled and exhaust plume lfow ifeld. With the compare between the simulation andexperiment of LH2/LOX rocket exhaust plume, the model is proved to be effective and correct. What’s more, the characteristic analysis of plume lfow ifeld between UDMH/NTO engine and LH2/LOX engine shows that tendency of temperature and mach number are the same, but the UDMH/NTO engine exhaust plume has a core of lower temperature and LH2/LOX engine exhaust plume attenuation to the subsonic lfow faster.