Numerical Simulation of Flow Field Characteristics of Supersonic Jet in Natural Cavitating Tail Cavity
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摘要: 为揭示自然空化尾空泡内超声速流场的演化规律与空泡内部的流场结构, 文中基于限体积法流体体积多相流模型, 对自然空化尾空泡内超声速射流流场展开仿真研究, 对比了不同空化数和来流攻角下的空泡内部流场参数分布, 得出如下结论: 自然空化尾空泡在超声速射流入射后, 空泡形态较稳定, 其演化主要集中在空泡尾部闭合处; 空泡内超声速射流流场发展主要受回射流影响, 无来流攻角时受回射流冲击, 射流轴向发展受抑, 轴向射流出现“回缩”现象, 有来流攻角时, 回射流位置发生偏移, 其剪切卷吸作用占主导, 射流轴向发展迅速; 航行器姿态的稳定性主要受来流冲击和表面高压区分布的影响, 空化数较小时, 增大来流攻角可大幅度增加航行器俯仰力矩。Abstract: In order to reveal the evolution law of the supersonic flow field in the natural cavitating tail cavity and the flow field structure in the cavity, this paper simulated the flow field of the supersonic jet in the natural cavitating tail cavity based on the volume of fluid (VOF) multiphase flow model. The paper compared the distribution of the flow field parameters in the cavity under different cavitation number and different angles of attack of incident flow, and drew the following conclusions: The cavity shape of the natural cavitating tail cavity is relatively stable after the incident flow of the supersonic jet, and its evolution is mainly concentrated in the closure of the cavity tail. The development of the flow field of the supersonic jet in the cavity is mainly affected by the re-entrant jet. When there is no angle of attack of incident flow, the flow field is impacted by the re-entrant jet, and the axial development of the jet is suppressed. The axial jet appears retracted phenomenon. When there is an angle of attack of the incident flow, the position of the re-entrant jet has shifted, and the shear and suction effect is dominant. The axial development of the jet is rapid, and the stability of the attitude of the vehicle is mainly affected by the impact of the incident flow and the distribution of the surface high-pressure area. When the cavitation number is small, increasing the angle of attack of the incident flow can greatly increase the pitching moment of the vehicle.
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Key words:
- natural cavitation /
- supersonic jet /
- tail cavity /
- flow field
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图 5 壁面压力实验与数值仿真结果对比曲线
Figure 5. Results of wall pressure between experiment and numerical simulation
图 6 数值仿真与实验结果对比
Figure 6. Comparison between numerical simulation results and experimental results
图 7 来流攻角0°、空化数0.06下不同时刻空泡形态轮廓
Figure 7. The outline of the cavity with different moments at the incident flow angle of attack 0° and cavitation number 0.06
图 10 空泡内射流中后期流场演化过程
Figure 10. Evolution of the flow field in the middle and late period of jet in the cavity
图 12 射流入射后空泡内部压力场分布
Figure 12. Distribution of the pressure field inside the cavitation after the jet injects
图 13 回射流冲击后航行器底部压力分布
Figure 13. Pressure distribution at the bottom of the vehicle after the impact of the re-entrant jet
图 15 射流核心区轴线监测点压力
Figure 15. Pressure of monitoring points on the axis of the core area of the jet
图 16 空化数0.06时不同攻角下射流流场相分布
Figure 16. Phase distribution of jet flow field under different angles of attack at cavitation number 0.06
图 18 不同来流攻角下回射流对超声速射流的影响
Figure 18. Effect of re-entrant jet on supersonic jet under different angles of attack of incident flow
图 19 空化数0.06时不同来流攻角下监测点P7压力值
Figure 19. Pressure of monitoring point P7 under different attack angles of incident flow with cavitation number 0.06
图 20 不同空化数和来流攻角下航行器表面空泡形态变化
Figure 20. Cavity shape on the surface of the vehicle under different cavitation numbers and angles of attack of incident flow
图 21 来流攻角影响下航行器力学特性
Figure 21. The mechanical characteristics of the vehicle under the influence of the incident flow angle of attack
图 22 航行器附体空泡及周围压力场分布
Figure 22. The distribution of the cavity and surrounding pressure field of the vehicle
图 23 不同空化数和来流攻角下航行器俯仰力矩随时间变化曲线
Figure 23. Curves of pitching moment of the vehicle with different cavitation numbers and angles of attack of incident flow
图 24 空化数0.04、来流攻角2°下航行器附体空泡及压力场变化
Figure 24. Changes in cavity on the surface of the vehicle and the surrounding pressure field with the cavitation number 0.04 and the attack angle of incident flow 2°
表 1 参数列表
Table 1. List of parameters
工况 空化数 来流攻角/(°) 0 0.06 0 1 0.06 2 2 0.06 4 3 0.04 0 4 0.04 2 5 0.04 4 6 0.02 0 7 0.02 2 8 0.02 4 
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