进气道出口可压缩附面层测量及其参数计算方法研究  

Measurement for Compressible Boundary-layer of Aircraft Inlet and Investigation on Parameters Calculation

作　　者：姜健[1] 史建邦[1] 李冰[1] 

机构地区：[1]中国飞行试验研究院发动机所,西安710089

出　　处：《科学技术与工程》2014年第22期95-100,共6页Science Technology and Engineering

摘　　要：为测量飞机进气道出口的可压缩附面层,在分析所需测量参数及探讨附面层参数计算方法的基础上,研制了附面层总压测量耙、总温测量耙。通过在公用测量段上安装附面层测量耙,对某飞机进气道在某高速风洞中进行了不同马赫数、攻角、侧滑角组合的吹风试验。17种组合工况的试验及计算结果表明:研制的附面层总压及总温测量耙应用效果较好;附面层参数计算方法准确,拟合后的附面层速度分布较为合理;该方法能够用于测量和评定进气道出口的可压缩附面层。To measue compressible boundary-layer at outlet of aircraft inlet,total-pressure and total-temperature measurement rakes were developed based on analyzing required measurement parameters and discussing parameters calculation methods.Wind tunnel tests were carried out to a certain aircraft inlet in a high-speed wind tunnel at different mach number and angle of attack and slip angle combined conditions by fixing rakes in public measurement set.Wind tunnel and calculation results of 17 combined conditions show that：application effect of developed total-pressure and total-temperature measurement rakes are very well,parameters calculation methods are accurate and distribution of fitted boundary layer speed is reasonable,the whole process can be used to measurement and evaluation for compressible boundary-layer.

关 键 词：进气道 附面层 测量耙 风洞试验 参数计算 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]