跨声速风洞高速段一体化数值模拟研究  

Integrated Numerical Simulation Research of High-speed Section in Transonic Wind Tunnel

作　　者：杨小川[1] 王运涛[1] 洪俊武[1] 黄知龙[2] 孙运强[2] 江雄[1] YANG Xiaochuan;WANG Yuntao;HONG Junwu;HUANG Zhilong;SUN Yunqiang;JIANG Xiong(Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心设备设计及测试技术研究所,绵阳621000

出　　处：《航空工程进展》2020年第1期92-102,共11页Advances in Aeronautical Science and Engineering

基　　金：国家重点研究发展计划项目(2016YFB0200700)

摘　　要：追求高亚声速经济巡航的民机、跨声速高机动特性的战斗机对高性能跨声速风洞的需求日趋紧迫,开展跨声速风洞高速段一体化数值模拟研究,对跨声速风洞设计具有一定的参考意义。通过非对称平板扩压器算例,初步验证计算方法的可行性,并对跨声速风洞高速段进行计算收敛评判方法、不同初始条件和槽壁扩张角等因素研究。结果表明:采用模型区前后两个监测点马赫数变化作为收敛判据,方法可行且模型区流场均匀;不同初始化条件对收敛结果总体影响较小,特别是各截面流场分布和槽道流动方向上,两者结果基本相同;跨声速状态槽壁扩张角0.3°得到的试验段模型区域流场品质较槽壁扩张角0.0°更均匀。For civil aviation aircraft with high subsonic economic cruising and fighter with high maneuverability at transonic speed,their demand for high-performance transonic wind tunnels is becoming more and more urgent,and integrated numerical simulation research of high-speed section in transonic wind tunnel which has certain reference significance for the design of transonic wind tunnel is analyzed.Through an example of an asymmetric flat plate diffuser,the feasibility of the calculation method is initially verified.At the same time,the convergence and evaluation methods for the high-speed section of the transonic wind tunnel,different initial conditions,and the expansion angle of the groove wall are studied.The results indicate that the changing of the Mach number of monitoring points in model section can be the numerical convergence criteria.The influence on velocity distribution at model section and streamline in slot with different initial conditions is negligible.Moreover,the slotted wall divergence angle 0.3°acquires more uniform flow fields than divergence angle 0.0°.

关 键 词：跨声速风洞 风洞设计 槽壁扩张角 试验段 TRIP3.0 收敛判据 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]