| 摘要: |
| 为改进隐身飞行器推进系统的气动性能，针对S弯进气道开展了设计和分析。基于数值模拟方法、代理模型和遗传算法构建了一套自动优化方法。在优化设计过程中，结合参数化建模、网格自动生成和改进(SST)湍流模型求解，应用优化方法对飞行器进行了多目标设计，得到了进气道的优化推荐构型。应用尺度自适应模拟(SAS)方法对优化进气道气动性能进行了全面和细致的分析。研究结果表明: SAS方法可以较好地模拟S弯进气道的流动，优化设计能够极大地改进S弯进气道的气动性能；相比原始设计，优化进气道设计点的总压畸变指数降低了16.3%，总压恢复系数提高了1.1%。 |
| 关键词: S弯进气道 优化方法 非设计点性能 剪切应力模型 尺度自适应模拟 |
| DOI： |
| 分类号:V211.3 |
| 基金项目:国家装备预研基金(9140A25010312HK0301)；国家自然基金资助项目(11202162)。 |
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| S-Duct Inlet Optimal Design and Analysis |
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GAN Wen-biao1,2,ZHOU Zhou1,XU Xiao-ping1,WANG Rui1,ZHANG Le1
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(1. Science and Technology on UAV Laboratory，Northwestern Polytechnical University，Xi’an 710072，China;2. Research Institute of Unmanned Aerial Vehicle，Beihang University，Beijing 100191，China)
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| Abstract: |
| To improve aerodynamic performance of propulsion system for stealth aircraft，S-shaped inlet is designed and analyzed. An automated design optimization method was built，based on computational fluid dynamics (CFD)，surrogate models and genetic algorithm. Combining parameterized solid model，grid auto-generation，modified Menter’s k-ω Shear Stress Transport (SST) turbulent model solver，S-shaped inlet is designed by multi-objective optimization. The optimal recommended configuration is obtained. The aerodynamic performance of optimized inlet is analyzed by Scale Adaptive Simulation (SAS) method on detail and refinement . The results show that SAS method is good at numerical simulation of S-shaped inlet flow. Design optimization can greatly improve the aerodynamic performance of S-shaped inlet. Compared with the original design，the distortion coefficient of optimized inlet is decreased by 16.3% and total pressure recovery factor increased by 1.1% at design point. |
| Key words: S-duct inlet Optimization method Off-design performance Shear Stress Transport Scale Adaptive Simulation |
