CAJ | 학술논문

介绍了安装有后移式微型后缘装置（Rearward Mini-TED）的NACA23012翼型流场结构的低雷诺数风洞实验结果。实验采用PIV技术采集了不同迎角时翼型周围的速度分布，测量了后缘附近 Mini-TED周围的详细涡旋结构，并与NACA23012原型翼型周围流场进行比较分析，以研究该 Mini-TED对翼面流动分离特性造成的影响，本实验以弦长为特征量的雷诺数为Re≈1．3×105。实验结果显示，Mini-TED对上翼面的流动分离有明显的抑制作用，尤其在较大迎角时更为有效，并且上翼面流速均高于对应迎角时原型翼型的翼面速度；下翼面流动在Mini-TED前方形成局部的低速区，造成静压升高，同时 Mini-TED 上方观察到对涡结构，形成低压区，二者共同作用的结果将导致后缘产生附加升力，增加翼型的低头力矩。上下翼面间的速度差比原型翼型有所增加，使翼型获得更高的升力。
개소료안장유후이식미형후연장치（Rearward Mini-TED）적NACA23012익형류장결구적저뢰낙수풍동실험결과。실험채용PIV기술채집료불동영각시익형주위적속도분포，측량료후연부근 Mini-TED주위적상세와선결구，병여NACA23012원형익형주위류장진행비교분석，이연구해 Mini-TED대익면류동분리특성조성적영향，본실험이현장위특정량적뢰낙수위Re≈1．3×105。실험결과현시，Mini-TED대상익면적류동분리유명현적억제작용，우기재교대영각시경위유효，병차상익면류속균고우대응영각시원형익형적익면속도；하익면류동재Mini-TED전방형성국부적저속구，조성정압승고，동시 Mini-TED 상방관찰도대와결구，형성저압구，이자공동작용적결과장도치후연산생부가승력，증가익형적저두력구。상하익면간적속도차비원형익형유소증가，사익형획득경고적승력。
The wind tunnel experimental results of flow structures of a NACA23012 airfoil mounted with a rearward Mini-TED for low Reynolds number situations are introduced in this pa-per.The PIV technique was applied to capture the velocity fields around the airfoil for different angle of attack,and the detailed vortex structures near the trailing edge were measured as well. The velocity measurement results are compared with those of NACA23012 prototype airfoil,so as to investigate the influence of the Mini-TED on the flow separation characteristics above the airfoil surface.The Reynolds number is Re≈1.3×105 based upon the chord length of the airfoil. The results show that the flow separation on the suction surface of the airfoil,especially for the case of larger angle of attack,is obviously depressed due to the installation of Mini-TED,and the flow speed on the suction surface is much higher than that of NACA23012 prototype airfoil.A low speed region is locally formed in front of the Mini-TED,which leads to the increase of static pressure.Meanwhile,a double-vortex structure with low pressure is observed behind the Mini-TED.The resulting pressure difference causes the extra lift increment near the trailing edge of the airfoil,and the pitching moment is increased as well.The velocity differences between the suction surface and the pressure surface of airfoil with the Mini-TED are higher than those of the NACA23012 prototype airfoil,which can contribute to the increment of lift force.