| 0.6m连续式跨声速风洞总体性能 |
| |
| 引用本文： | 廖达雄,陈吉明,郑娟,陈钦,裴海涛,吴盛豪.0.6m连续式跨声速风洞总体性能[J].实验流体力学,2018,32(6):88-93. |
| |
| 作者姓名： | 廖达雄 陈吉明 郑娟 陈钦 裴海涛 吴盛豪 |
| |
| 作者单位： | 1.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： | 中国空气动力研究与发展中心（CARDC）0.6m连续式跨声速风洞是一座采用干燥空气作为试验介质的变密度回流式风洞，设计方案采用了宽工况压缩机及其与风洞一体化设计、半柔壁喷管、低噪声跨声速试验段、指片再入调节片式主流引射缝、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。通过风洞总体性能调试，获取了风洞安全运行边界及总体性能，得到了风洞各关键部段性能参数。调试结果表明，风洞总体和各部段性能均达到预期设计技术要求；压缩机、换热器和各辅助系统设备运行性能良好；实现稳定段总压运行范围15~250kPa，总压控制精度优于0.2%；实现试验段Ma运行范围为0.144~1.640，马赫数控制精度优于0.002；轴向马赫数分布均方根偏差优于设计指标（Ma ≤ 1.0时，σMa < 0.002，1.0 < Ma ≤ 1.6时，σMa < 0.008）的要求；当试验Ma ≥ 0.5时，试验段核心气流脉动压力系数ΔCp < 0.8%。调试结果验证了0.6m连续式跨声速风洞设计方案的可行性，为我国大型连续式跨声速风洞研制提供参考。
|
| 关 键 词： | 连续式跨声速风洞 总体性能 槽壁试验段 流场品质 风洞调试 |
| 收稿时间： | 2017-06-28 |
General performance of 0.6m continuous transonic wind tunnel |
| |
| Affiliation: | 1.State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China2.Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China |
| |
| Abstract: | The 0.6m continuous transonic wind tunnel of CARDC, a circling wind tunnel, use dry air in variable density as working medium. The major components of the wind tunnel include broad-performance compressor, semi-flexible nozzle, lower-noise test section, re-entry flaps and slots, heat-exchange system and the second throat with wall flaps and center body. In order to get the general performance and the secure running boundary of the wind tunnel, the general performance calibration is carried out. Calibration results indicate that the general performances and each section of the wind tunnel agree well with the requirements. The compressor, heat-exchange system and other auxiliary equipments are all in working order. The range of total pressure in settling chamber is 15~250kPa and the control precision of the total pressure is better than 0.2%. The Mach number in the test section is in the range of 0.144~1.640 and the control precision of the Mach number is better than 0.002. The flow qualities such as the fluctuation of Mach number distribution have met the requirements(Ma ≤ 1.0, σMa < 0.002;1.0 < Ma ≤ 1.6, σMa < 0.008). When the Mach number is greater than 0.5, the flow fluctuation coefficient which is used to represent the noise level is below 0.8%. The design scheme's feasibility of the 0.6m continuous transonic wind tunnel is fully verified by the debugging results, which provide scientific guidance for the development of the large-scale continuous transonic wind tunnel. |
| |
| Keywords: | |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《实验流体力学》浏览原始摘要信息 |
|
点击此处可从《实验流体力学》下载全文 |
|
