荧光油流摩擦力场测量试验

Experimental studies of luminescent oil flow skin friction measurement

飞行器表面摩擦阻力测量是空气动力学领域的研究难点。在风洞试验中有多种摩擦力测量方法,但多为单点式测量,试验中采用荧光油流摩擦力场测量技术在低速开口式风洞中对平板翼型和RAE2822二元翼型的上表面摩擦力分布情况进行了测量。试验结果表明:该测量技术可以测得模型表面的摩擦力信息,所得平板流场层流部分的摩擦力信息与布拉修斯(Blasius)层流解趋势一致,并得到二元翼型三维摩擦力信息及某一沿流向剖面的τ-x曲线。

The skin friction measurement of aircraft surface has always been a difficulty in aerodynamics field. There are a variety of friction measuring methods in wind tunnel test,most of which are almost single point measurement methods. The surface friction distribution on a flat plate model and a 2-D airfoil RAE2822 model was tested by fluorescence oil flowfriction field measurement technology in lowspeed wind tunnel. The results showthat the skin friction information on the model surface can be obtained by the measurement technology and the friction force information and Blasius laminar flowsolution is consistent in this flat plate situation,and we can get the 3-D friction information on the RAE2822 model surface and a τ-x curve along the flowprofile.