超音速校准风洞中的喷管设计  

Design of Nozzles in a Supersonic Calibration Wind Tunnel

作　　者：荆卓寅[1] 赵俭[1] 李海燕[1] 

机构地区：[1]中航工业北京长城计量测试技术研究所,北京100095

出　　处：《计测技术》2016年第5期18-22,共5页Metrology & Measurement Technology

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。本文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。With the development of the aviation technology,it is necessary to construct a supersonic calibration wind tunnel which meets the needs of dynamic calibration of sensors. 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,and meet the requirements of a supersonic wind tunnel calibration.

关 键 词：超音速喷管 特征线法 附面层修正 

分 类 号：TB942[一般工业技术—计量学]