| 连续式跨声速风洞设计关键技术 |
| |
| 引用本文： | 廖达雄,陈吉明,彭强,柳新民.连续式跨声速风洞设计关键技术[J].气动实验与测量控制,2011(4):74-78. |
| |
| 作者姓名： | 廖达雄 陈吉明 彭强 柳新民 |
| |
| 作者单位： | 中国空气动力研究与发展中心空气动力学国家重点实验室,四川绵阳621000 |
| |
| 摘 要： | 为研制先进飞行器，除了提高现有风洞试验测量精度和改进试验技术外，必须建立高性能连续式跨声速风洞试验设备，解决飞行器高速风洞试验模拟能力和精细化模拟问题。以试验段尺寸0．6m×0．6m连续式跨声速风洞设计为例，给出了风洞总体设计方案，分析了如何降低风洞气流脉动、如何改善风洞流场品质、提高风洞运转效率和拓展风洞试验能力等关键技术途径。该风洞作为大型连续式跨声速风洞的引导风洞，方案设计主要采用了高压比压缩机驱动系统、半柔壁喷管、低噪声试验段、高性能换热器和三段调节片加可调中心体式二喉道等新型技术。
|
| 关 键 词： | 连续式风洞 跨声速风洞 低噪声 风洞设计 关键技术 |
Key design techniques of the low noise continuous transonic wind tunnel |
| |
| Authors: | LIAO Da-xiong CHEN Ji-ming PENG Qiang LIU Xin-min |
| |
| Institution: | 1. State Key Laboratory of Aerodynamics,Mianyang Sichuan 621000,China;2. Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center, Mianyang Sichuan 621000,China) |
| |
| Abstract: | In order to develop advanced aircrafts, the high-performance continuous transonic wind tunnel should be constructed to get test simulation capability and to reach a refined simulation for the aircraft in high-speed wind tunnel except that the measurement accuracy of current wind tunnel tests and the testing techniques should be improved. This paper presents the general design project of the 0.6m low-noise continuous transonic wind tunnel. The measures to reduce the flow pulsation, improve the flow quality, increase the operation efficiency and to unfold the test capability are put forward. The 0.6m wind tunnel is the pilot tunnel of the large continuous transonic wind tunnel. The high-pressure-ratio axis-flow compressor, the flexible nozzle, the lownoise test section, the high-performance heat exchanger and the second throat are utilized in the design project. |
| |
| Keywords: | continuous wind tunnel transonic wind tunnel low noise wind tunnel design key technique |
| 本文献已被 维普 等数据库收录！ |
