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胡文杰, 邱云龙, 邹昊, 吴昌聚, 陈伟芳. 高速飞行器边界层质量引射降热减阻技术流量分区优化研究. 力学学报, 2024, 56(6): 1-14. DOI: 10.6052/0459-1879-23-512
引用本文: 胡文杰, 邱云龙, 邹昊, 吴昌聚, 陈伟芳. 高速飞行器边界层质量引射降热减阻技术流量分区优化研究. 力学学报, 2024, 56(6): 1-14. DOI: 10.6052/0459-1879-23-512
Hu Wenjie, Qiu Yunlong, Zou Hao, Wu Changju, Chen Weifang. Optimization study of boundary layer mass injection flow rate by zonal divisions for heat and drag reduction of high-speed vehicles. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(6): 1-14. DOI: 10.6052/0459-1879-23-512
Citation: Hu Wenjie, Qiu Yunlong, Zou Hao, Wu Changju, Chen Weifang. Optimization study of boundary layer mass injection flow rate by zonal divisions for heat and drag reduction of high-speed vehicles. Chinese Journal of Theoretical and Applied Mechanics, 2024, 56(6): 1-14. DOI: 10.6052/0459-1879-23-512

高速飞行器边界层质量引射降热减阻技术流量分区优化研究

OPTIMIZATION STUDY OF BOUNDARY LAYER MASS INJECTION FLOW RATE BY ZONAL DIVISIONS FOR HEAT AND DRAG REDUCTION OF HIGH-SPEED VEHICLES

  • 摘要: 边界层质量引射被认为是解决临近空间高超声速飞行器关键部位热防护问题和减小其飞行阻力的有效途径之一. 然而, 已有研究主要关注边界层质量引射对热流或阻力的单独影响, 少有研究对边界层质量引射能够带来的降热减阻效果进行综合评估. 针对高空高超声速层流条件下钝楔与钝锥外形的边界层质量引射降热减阻问题开展数值模拟研究, 并采用多目标优化方法开展了边界层质量引射的分区流量优化设计, 在满足减阻性能的同时, 提高了整体的热防护效果, 实现了给定冷却剂流量条件下的降热减阻综合性能优化. 研究结果表明, 层流条件下, 边界层质量引射通过改变速度边界层和温度边界层能够显著降低壁面摩阻和热流. 在单位面积引射质量流量为28.028g/(m2·s)时, 对于钝楔外形, 采用均匀引射方案能够减阻3.60%, 同时峰值热流下降12.06%, 而采用分区优化方案能够将减阻效果提高到4.30%, 同时峰值热流下降91.01%; 对于钝锥外形, 采用均匀引射方案会造成阻力增大2.60%, 同时峰值热流仅下降8.57%, 而采用分区优化方案能够在减阻19.75%的情况下同时将峰值热流降低99.95%.

     

    Abstract: Boundary layer mass injection is considered to be one of the most effective strategies for solving the thermal protection problem of critical parts of hypersonic vehicles in near-space and reducing their flight drag. However, most existing studies focused on the individual effects of boundary layer mass injection on heat flux or drag, and rarely provided a comprehensive assessment of the heat and drag reduction effects that can be brought about by boundary layer mass injection. In this paper, a numerical simulation study is carried for investigating the heat and drag reduction induced by boundary layer mass injection with blunt wedge and blunt cone under high-altitude hypersonic laminar flow conditions. A multi-objective optimization method is adopted to carry out the optimized design of the mass flow rate distribution for boundary layer mass injection, which can satisfy the drag reduction performance and at the same time improve the overall thermal protection effect, thus realizing optimal integrated performance of heat and drag reduction under the circumstance of a specific coolant mass flow rate. The results show that under laminar flow conditions, boundary layer mass injection can significantly decrease the skin friction and heat flux by adjusting the velocity boundary layer and the temperature boundary layer. For the blunt wedge with an injection mass flow rate of 28.028 g/(m2·s), the design with uniform mass flow rate distribution decreases the drag by 3.60% and the peak heat flux by 12.06%, while the optimization design decreases the drag by 4.30% and the peak heat flux by 91.01%. However, for the blunt cone with a same injection mass flow rate of 28.028 g/(m2·s), the design with uniform mass flow rate distribution increases the drag by 2.60% and decreases the peak heat flux only by 8.57%, while the optimization design decreases the drag by 19.75% and the peak heat flux by 99.95%.

     

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