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丛成华,任泽斌,李松.高速风洞起动特性数值模拟[J].航空动力学报,2020,(7):1361~1368
高速风洞起动特性数值模拟
Numerical simulation about starting process characteristics of hypersonic wind tunnel
投稿时间:2019-12-16  
DOI:10.13224/j.cnki.jasp.2020.07.003
中文关键词:  高速风洞  起动过程  激波结构  激波串  试验舱  收集器  溢流  非定常模拟
英文关键词:hypersonic wind tunnel  starting process  shock structure  shock train  ,test cabin  pickup collector  overfall  unsteady simulation
基金项目:空气动力学国家重点实验室基金(JBKY15040205); 江苏高校优势学科建设工程资助项目
作者单位
丛成华 Key Laboratory of Unsteady Aerodynamics and Flow Control of Ministry of ,Industry and Information TechnologyCollege of Aerospace Engineering,,Nanjing University of Aeronautics and AstronauticsNanjing 210016,China
Facility Design and Instrumentation Institute,,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China 
任泽斌 Facility Design and Instrumentation Institute,,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China 
李松 Facility Design and Instrumentation Institute,,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China 
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中文摘要:
      为获得高速风洞起动过程中的流场结构变化特性,采用数值模拟方法,使用二维轴对称模型对Φ 05 m高速风洞喷管段、试验段和扩压器段的流场特性进行了研究,控制方程为黏性可压缩非定常Navier-Stokes方程。对试验段马赫数为5和10两种状态下的流场建立过程进行了对比,结果表明,在风洞起动过程中,喷管内的附面层很厚,激波与附面层相互作用形成复杂的激波结构。试验段马赫数为5时在喷管段形成正激波,试验段马赫数为10时自喷管段形成激波串,起动压比低于按照正激波理论所计算得到的压比。激波串的起动速度较正激波慢,但稳定性较正激波好。起动过程中,气流发生过度欠膨胀,波前瞬时马赫数远大于喷管的设计马赫数。喷管出口的自由射流与收集器作用复杂,收集器溢流对试验段建立稳定的流动起关键作用。
英文摘要:
      In order to obtain the characteristics of the flow field structure changes during the starting progress of the hypersonic wind tunnel, two-dimensional axisymmetric model was used to study the flow field characteristics of the nozzle section, test section and diffuser section of the Φ05 m high speed wind tunnel. The governing equations were the conservational Navier-Stokes equations, which described viscous, compressible and unsteady flows. The establishment process of flow field at test section Mach number 5, 10 was compared, and the results showed that the boundary layer in the nozzle was very thick, and the complex shock structure was formed by the interaction of shock wave and boundary layer. When test section Mach number was 5, a positive shock wave was formed in the nozzle section. When the test section Mach number was 10, a shock wave string was formed from the nozzle section. The starting pressure ratio was lower than that calculated according to the positive shock theory. The starting speed of the shock wave string was slower than that of the positive shock, but its stability was better than that of the positive shock. During the starting process, the flow underexpanded excessively, and the instantaneous Mach number of the wave front was much larger than the design Mach number of the nozzle. The free jet at the exit of the nozzle and the collector played a complex role. The overfall of the collector played a key role in establishing a stable flow in the test section.
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