In order to predict the distribution of sound fields of the jet noise of a rocket engine , we performed the numerical simulation of the aerodynamic sound field of the noise of high -temperature jet of nozzles of different sizes and analyzed the characteristics of the sound field .Then, we designed the three types of nozzles with the same out -let Mach number but different sizes and simulated their jet noise and analyzed its sound field distribution and the effects of nozzle sizes on the jet noise of a rocket engine .The simulation results, given in Figs.5 through 9, and their analysis show preliminarily that : (1) the noise at the far field of the jet is directional ; (2) the sound pressure level of the jet noise reaches maximum at the angle of 40°away from the jet center axis; (3) the sound pressure lev-el of the jet noise sound field increases with increasing nozzle sizes .% 为了研究喷管尺寸对火箭发动机喷流噪声声场分布的影响规律，采用 LES 与 FW-H 相结合的方法，针对不同喷管尺寸的高温燃气喷流气动声场进行了数值模拟，并分析了声场特性。数值结果表明，火箭发动机喷流远场噪声具有方向性，噪声声压级在离开喷流中心轴线40°处达到最大值；喷流噪声声场的声压级随着喷管尺寸的增大而增加。研究结果为不同尺寸的火箭发动机喷流噪声预测提供参考依据。
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