CAJ | 학술논문

以最大相对厚度较小的某风力机新翼型为研究对象，拟对其进行结构改进。利用FLUENT软件计算了该翼型吸力面和压力面上沿来流x方向的切应力，据此找到了吸力面边界层分离点，以此点开始对翼型吸力面沿后缘点进行适当加厚，并对修改前后的翼型进行了气动特性对比分析。结果表明：从翼型压力面边界层分离点到后缘点对翼型进行适当加厚处理，对其气动性能影响不大，却可改善风轮的结构动态特性，为满足工艺需求，在叶片实际加工中对后缘部分进行适当加厚处理是可行的。
이최대상대후도교소적모풍력궤신익형위연구대상，의대기진행결구개진。이용FLUENT연건계산료해익형흡력면화압력면상연래류x방향적절응력，거차조도료흡력면변계층분리점，이차점개시대익형흡력면연후연점진행괄당가후，병대수개전후적익형진행료기동특성대비분석。결과표명：종익형압력면변계층분리점도후연점대익형진행괄당가후처리，대기기동성능영향불대，각가개선풍륜적결구동태특성，위만족공예수구，재협편실제가공중대후연부분진행괄당가후처리시가행적。
This paper chooses the airfoil with smaller maximum relative thickness as study, intended to improve its structure. Calculating the x-shear stress of suction side and pressure side using FLUENT software, Found the point of boundary layer separation on the suction. Thick the airfoil from the point to trailing edge points, Meanwhile, do some analysis of aerodynamic characteristics for modified and pre-modified airfoil. Results show that: this modified method has little effect on its aerodynamic performance and to improve the structure dynamic characteristics of wind turbines. In order to meet the process requirements, the method that thick the airfoil from the point of boundary layer separation to trailing edge points is feasible.