双旁侧无隔道超声速进气道参数化设计及流动分析

Parametric Design and Flow Analysis of Dual-Lateral Diverterless Supersonic Inlet

针对双旁侧无隔道超声速进气道中S弯流道内部流向涡产生的大畸变问题,提出了参数化设计技术,并基于典型飞机前体设计进气道构型,利用Liutex涡识别技术分析S弯流道内部的流动机理,并探索提升进气道出口流场品质的设计技术。研究结果表明:Liutex涡识别理论在进气道流场中能够有效识别流向涡的大小和强度;为抑制流向涡的产生和发展,降低出口畸变,进气道入口处上唇口一侧流道应采用较小的曲率,下唇口一侧则需要增大曲率;S弯流道末端应增大扭曲程度以将流向涡推至进气道出口中间区域。本文研究可有效抑制无隔道超声速进气道出口畸变,为控制S弯流道内部流向涡结构探索新型设计方法。

In view of the large distortion caused by streamwise vortex in the S-bend of dual-lateral diverterless supersonic inlet, a parametric design method was proposed, and an inlet configuration was designed based on the typical aircraft forebody. The flow mechanism inside the S-bend was analyzed by using Liutex vortex identification method, and the design method was explored to improve the flow field quality of inlet. The results show that the Liutex vortex identification method can effectively identify the size and intensity of streamwise vortex in the flowfield of the S-bend. In order to suppress the generation and development of streamwise vortex and reduce the distortion of the outlet, the configuration on the upper lip side at the inlet entrance should have a smaller curvature, and on the lower lip side curvature should be increased. The end of the flow channel should be twisted to push the streamwise vortex into the centre of the outlet. The study can effectively suppress the distortion of the outlet, and explore a new design method to control the streamwise vortex inside the flow channel.