CAJ | 학술논문

以微小型无人机翼型研究为背景，开展了低雷诺数翼型的气动特性及优化设计研究。首先采用求解雷诺平均 N?S 方程的有限体积法，对典型低雷诺数下 NACA0012翼型标模进行数值模拟，对比分析了 SA、SST k?ω湍流模型、低雷诺数修正 SST k?ω模型以及 k?kL?ω转捩模型的适用性和准确性。然后通过对低雷诺数下 NACA0012翼型表面流场结构和流动特征的详细分析，提出了基于控制流动转捩位置改善翼型上边界层形态的低雷诺数翼型设计思想。最终基于转捩模型对 SD7037翼型进行了多目标优化设计，设计结果表明优化后翼型气动性能得到了较大改善，最大升阻比可以提高约58．23％，在0°迎角下翼型上表面层流区域面积增大约26．8％，在4°迎角下翼型上表面流动转捩位置前移约0．15倍弦长，下游流动亦由优化前完全分离状态改变为实现流动再附，进一步验证了低雷诺数翼型设计思路的可靠性与可行性。
이미소형무인궤익형연구위배경，개전료저뢰낙수익형적기동특성급우화설계연구。수선채용구해뢰낙평균 N?S 방정적유한체적법，대전형저뢰낙수하 NACA0012익형표모진행수치모의，대비분석료 SA、SST k?ω단류모형、저뢰낙수수정 SST k?ω모형이급 k?kL?ω전렬모형적괄용성화준학성。연후통과대저뢰낙수하 NACA0012익형표면류장결구화류동특정적상세분석，제출료기우공제류동전렬위치개선익형상변계층형태적저뢰낙수익형설계사상。최종기우전렬모형대 SD7037익형진행료다목표우화설계，설계결과표명우화후익형기동성능득도료교대개선，최대승조비가이제고약58．23％，재0°영각하익형상표면층류구역면적증대약26．8％，재4°영각하익형상표면류동전렬위치전이약0．15배현장，하유류동역유우화전완전분리상태개변위실현류동재부，진일보험증료저뢰낙수익형설계사로적가고성여가행성。
Based on the research of the micro air vehicle (MAV), the aerodynamic performances and optimization design of the low Reynolds number airfoil were numerically simulated and studied. To verify the accuracy and relia?bility respectively of the SA, SST k?ω turbulence model, low Reynolds corrected SST k?ω model and k?kL?ω transi?tion model, finite volume method was used to solve the 2D Reynolds?averaged Navier?Stokes equations for the nu?merical simulations of the fluid flow around NACA0012 in representative Reynolds numbers. Then the low Reynolds number flow characteristics of the fluid structures and flow mechanism around NACA0012 were studied. And at last an optimization mind for the low Reynolds number airfoil design was proposed, tested by a multi?objective optimiza?tion case of SD7037. The optimization results showed that 58. 23% increment of lift to drag ratio, 26. 8% increment of laminar flow area at α= 0°, 0. 15c forward movement of transition position and the reattachment downstream can be achieved; this can verify the reliability and feasibility of the optimization mind.