基于嵌套网格变几何轴对称进气道非定常数值模拟  

Unsteady numerical simulation of variable geometry axisymmetric inlet based on overset grid

作　　者：罗炯 李志宏 陈科[1] 向欢 LUO Jiong;LI Zhihong;CHEN Ke;XIANG Huan(AVIC Chengdu Aircraft Design and Research Institute,Chengdu 610091,China)

机构地区：[1]航空工业成都飞机设计研究所,成都610091

出　　处：《航空学报》2022年第12期25-33,共9页Acta Aeronautica et Astronautica Sinica

基　　金：省部级项目。

摘　　要：涡轮/冲压组合动力需要在宽马赫数范围良好工作,定几何进气道性能难以满足要求。轴对称进气道可通过前后移动中心锥进行进气道的动态调节,使进气道在宽马赫数范围内良好工作。通过嵌套网格技术对轴对称进气道动态调节过程进行非定常数值模拟,分析轴对称进气道在动态调节过程中起动性能和总压恢复变化规律。计算结果表明:定常计算中随着进气道出口反压增加,进气道结尾激波不断向前移动,当反压超过临界状态时,进气道处于不起动状态;非定常计算动态调节过程,进气道均处于起动状态,进气道性能略微降低。The axisymmetric inlet can improve the performance of the whole operating range through the scheme of translating the whole spike.The unsteady flow field of the dynamic regulation process of axisymmetric inlet was simulated by the overset grid approach in this study.The changing rule of start performance and the total pressure recovery coefficient in the dynamic regulation process of the inlet was studied through simulation.The results show that the inlet terminal shock wave moves forward with the increase of the anti-back pressure under the steady condition.With the back pressure exceeding a critical level,the inlet remains unstarted.In the unsteady regulation simulation,the inlet works in the starting mode with slightly lower performance.

关 键 词：嵌套网格 变几何 动态调节 轴对称进气道 非定常 

分 类 号：V221.1[航空宇航科学与技术—飞行器设计]