CAJ | 학술논문

　　采用类别形状函数变换（CST）方法对翼型参数化描述；利用Fluent软件，进行翼型升力系数和阻力系数的气动计算；以升阻比最大为优化目标，通过拉丁超立方设计生成样本点，建立了径向基神经网络（RBF）代理模型；使用粒子群优化算法（PSO），在Isight平台上，实现对Clark Y翼型优化的整个过程。优化翼型升阻比比原始翼型提高了约10%，表明此种方法是可行的，可用于小型无人机设计的工程中。
　　채용유별형상함수변환（CST）방법대익형삼수화묘술；이용Fluent연건，진행익형승력계수화조력계수적기동계산；이승조비최대위우화목표，통과랍정초립방설계생성양본점，건립료경향기신경망락（RBF）대리모형；사용입자군우화산법（PSO），재Isight평태상，실현대Clark Y익형우화적정개과정。우화익형승조비비원시익형제고료약10%，표명차충방법시가행적，가용우소형무인궤설계적공정중。
The CST universal parametric geometry representation method was used to describe the parametric air? foil,and lift coefficient and drag coefficient of the designed airfoil was directly calculated by Fluent. The maxi? mum lift-drag ratio as the goal was achieved by employing PSO algorithm. The latin hypercube method was em? ployed to construct the initial sample points used in a RBF surrogate model. The software of Isight was used to realize the design processes. The maximum lift-drag ratio was significantly improved by about 10%. The result showed that this approach was feasible and could be used as reference for Mini-UAV design in engineering.