Numerical study of supersonic jet flow field characteristics 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VOF多相流模型, 对自然空化尾空泡内超声速射流流场展开研究, 分析了空泡内超声速射流流场的演化规律, 对比了不同空化数以及不同来流攻角下的空泡内部流场参数的分布, 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; 航行体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体俯仰力矩。Abstract: In order to reveal the evolution law of the supersonic flow field in the cavitation tail cavitation tail and the flow field structure inside the cavitation bubble, this paper studies the supersonic jet flow field in the cavitation tail cavitation tail based on the VOF multiphase flow model, analyzes the evolution law of the supersonic jet flow field in the cavitation, compares the distribution of the flow field parameters in the cavitation under different cavitation numbers and different incoming flow angles, and draws the following conclusions: the cavitation morphology of the natural cavitation tail cavitation bubble is relatively stable after the inflow of supersonic jet, and its evolution is mainly concentrated in the closure of the cavitation tail; When there is an incoming angle of attack, the position of the backjet is shifted, and its shear and suction effect is dominant, and the axial development of the jet is rapid; the stability of the attitude of the aircraft is mainly affected by the impact of the incoming flow and the distribution of the surface high pressure area, and when the cavitation number is small, increasing the angle of attack of the incoming flow can greatly increase the pitching moment of the aircraft.
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Key words:
- natural cavitation /
- supersonic jet /
- tail cavity /
- numerical research
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图 5 壁面压力实验与数值模拟对比图
Figure 5. Comparison of wall pressure experiment and numerical simulation
图 6 数值模拟结果与实验结果对比
Figure 6. Comparison of numerical simulation results with experimental results
图 7 来流攻角0°空化数0.06不同时刻空泡形态轮廓
Figure 7. Inflow angle 0° cavitation number 0.06 cavitation shape profile at different times
图 10 空泡内射流中后期流场演化过程
Figure 10. The evolution process of the flow field in the middle and late period of the cavity jet
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 回射流冲击后航行体底部压力分布
Figure 13. Pressure distribution at the bottom of the vehicle after the impact of the retro jet
图 15 射流核心区轴线监测点压力
Figure 15. Pressure at the monitoring point on the axis of the core area of the jet
图 16 空化数0.06不同攻角射流流场相分布
Figure 16. Cavitation number 0.06 Phase distribution of jet flow field at different angles of attack
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 backjet on supersonic jet under different angles of attack
图 19 空化数0.06不同来流攻角下监测点P7压力值
Figure 19. Cavitation number 0.06 P7 pressure value of monitoring point at different inlet attack angles
图 20 不同空化数和来流攻角下航行体表面空化泡分布
Figure 20. Distribution of cavitation bubbles on the surface of the vehicle under different cavitation numbers and incoming angles of attack
图 21 来流攻角下航行体力学分布特性
Figure 21. Schematic diagram of the attitude change of the aircraft hull
图 22 航行体附体空泡及周围压力场的分布
Figure 22. The distribution of cavitation and surrounding pressure field in the body of the vehicle
图 23 不同空化数及来流攻角下航行体俯仰力矩随时间的变化
Figure 23. Variation of pitching moment of the vehicle with different cavitation numbers and incoming angles of attack
图 24 空化数0.04来流攻角2°航行体附体空泡及周围压力场的变化
Figure 24. The cavitation number is 0.04, the angle of attack is 2°, changes in cavitation on the surface of the vehicle and the surrounding pressure field
表 1 参数列表
Table 1. List of parameters
工况 空化数σ 来流攻角 Case0 0.06 0° Case1 0.06 2° Case2 0.06 4° Case3 0.04 0° Case4 0.04 2° Case5 0.04 4° Case6 0.02 0° Case7 0.02 2° Case8 0.02 4° 
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