| 超音速校准风洞中的超音速喷管设计 |
| Design of Nozzles in a Supersonic Calibration Wind Tunnel |
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| 中文摘要: |
| 随着航空技术的发展，需要建设超音速校准风洞，以满足传感器的相关校准需求。根据超音速喷管设计的一般原则和特征线理论以及附面层修正的方法，进行固定马赫数的超音速喷管设计，并对设计的喷管形面进行了数值仿真，结果表明该方法能够实现设计要求，满足超音速校准风洞的使用要求。 |
| 英文摘要: |
| With the development of the aviation technology,the construction of a supersonic calibration wind tunnel which meets the needs of dynamic calibration of sensors is needed.According to the general principle of supersonic nozzle design, the characteristic line theory and the method of boundary layer correction,the design of supersonic nozzle with fixed Mach number is carried out.Surface shape and design of the nozzle numerical simulation results show that this method can achieve the design requirements, to meet the requirements of a supersonic wind tunnel calibration. |
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| 中文关键词: 超音速喷管 特征线法 附面层修正 |
| 英文关键词:supersonic nozzle the characteristic line theory the method of boundary layer correction |
| 基金项目: |
| DOI：10.11823/j.issn.1674-5795.2016.05.05 |
| 引用本文：荆卓寅ꎬ,赵俭ꎬ,李海燕.超音速校准风洞中的超音速喷管设计[J].计测技术,2016,36(5):. |
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