CAJ | 학술논문

将风力机翼型气动性能与气动噪声同时作为翼型优化目标,建立了低速翼型的多目标优化设计方法,包括利用Bezier曲线对翼型几何结构进行参数化建模,使用位势流动与边界层迭代（IBL）的流动分析方法计算翼型流场,采用Brooks-Pope-Marcolini翼型自噪声半经验模型预测气动噪声,利用Powell优化方法求得优化翼型.以naca0012翼型为例,对多种目标权重分配方案的优化目标进行设计和计算.结果表明：与原始翼型相比,在设计工况下,优化翼型的升阻比提高,噪声降低,可以获得更好的气动性能和声学性能.
장풍력궤익형기동성능여기동조성동시작위익형우화목표,건립료저속익형적다목표우화설계방법,포괄이용Bezier곡선대익형궤하결구진행삼수화건모,사용위세류동여변계층질대（IBL）적류동분석방법계산익형류장,채용Brooks-Pope-Marcolini익형자조성반경험모형예측기동조성,이용Powell우화방법구득우화익형.이naca0012익형위례,대다충목표권중분배방안적우화목표진행설계화계산.결과표명：여원시익형상비,재설계공황하,우화익형적승조비제고,조성강저,가이획득경호적기동성능화성학성능.
Taking both the aerodynamic and aeroacoustic performance as the objectives of optimization, a multi-objective optimization method was proposed for low-speed airfoils by using Bezier curves to describe the airfoil geometry, applying the analysis method of iterative potential flow and boundary layer （IBL） flow to calculate the flow field, using the Brooks-Pope-Marcolini airfoil self-noise semi-empirical model to predict the aerodynamic noise and adopting Powell method to obtain the optimized airfoil. The multi-objective optimization method has been verified with a NACA0012 prototype airfoil in different weight assignment schemes. Results show that compared with the prototype airfoil, the optimized one has a higher liftdrag ratio, lower acoustic level and better aerodynamic and aeroacoustic performance under design condi- tions.