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针对传统概念设计的蛇形进气道畸变大、总压恢复系数较低以及相应流场控制技术存在局限性等缺点,对典型蛇形进气道内通道二次流的涡动力学形成及其对气流分离影响分析的基础上,提出了蛇形进气道涡控设计概念,并利用数值仿真进行了初步验证。仿真结果表明:与原型方案相比,蛇形进气道涡控设计方案成功抑制了上壁面大范围的气流分离,巡航状态畸变指数DC60降低了76%,总压恢复系数提高了0.84%,并且能够在较宽广的飞行包线内以较高的性能安全工作,表明了涡控设计概念的可行性。同时,由于涡控设计概念无需添加任何辅助的流场控制措施,因此有望使蛇形进气道迈向工程实用。
In view of the traditional concept of the design of the serpentine inlet distortion, the total pressure recovery coefficient is low and the corresponding flow field control technology limitations and other shortcomings, the typical serpentine inlet passage secondary flow eddy dynamics and its Based on the analysis of influence of airflow separation, the concept of vortices design of serpentine inlet was put forward, and the numerical simulation was used to verify the design. The simulation results show that compared with the prototype scheme, the design of the serpentine inlet vortex control successfully restrain the large-scale airflow separation on the upper wall surface, the cruising state distortion index DC60 is reduced by 76% and the total pressure recovery coefficient is increased by 0.84% The ability to work safely with higher performance in a wider flight envelope shows the feasibility of a vortex control design concept. At the same time, it is expected that the serpentine intake will be practical in engineering because the vortex control design concept does not need to add any auxiliary flow control measures.