CAJ | 학술논문

采用数值模拟的方法研究了旋转圆柱对 NACA0015翼型气动特性的影响，着重分析了前缘旋转圆柱转速比和缝隙大小对翼型升阻特性的作用规律以及不同安装位置的高速旋转圆柱结合简单襟翼偏转下的翼型气动力特性。结果表明，高速旋转的圆柱代替翼型前缘可以有效地抑制翼型背风区的流动分离，延缓边界层的发展从而改善翼型气动特性。前缘旋转圆柱理想的转速比在4附近，缝隙在2．5mm 至1．5mm 之间可以满足使用要求。简单襟翼结合前、后缘高速旋转圆柱情况下翼型的气动力特性可以比拟精心设计的多段翼型。旋转圆柱具有增升减阻效果显著，需要主动输入的能量极少等优点，是一种具有良好应用前景的边界层流动控制技术。
채용수치모의적방법연구료선전원주대 NACA0015익형기동특성적영향，착중분석료전연선전원주전속비화봉극대소대익형승조특성적작용규률이급불동안장위치적고속선전원주결합간단금익편전하적익형기동력특성。결과표명，고속선전적원주대체익형전연가이유효지억제익형배풍구적류동분리，연완변계층적발전종이개선익형기동특성。전연선전원주이상적전속비재4부근，봉극재2．5mm 지1．5mm 지간가이만족사용요구。간단금익결합전、후연고속선전원주정황하익형적기동력특성가이비의정심설계적다단익형。선전원주구유증승감조효과현저，수요주동수입적능량겁소등우점，시일충구유량호응용전경적변계층류동공제기술。
Moving surface boundary layer control technique appears quite promising for en—hancing the airfoils aerodynamics prominently with little energy input.Numerical simulations are conducted on the NACA0015 airfoil with rotating cylinders.The ratio of cylinder surface speed to the freestream speed as well as the gap between the cylinder and the fixed section are analyzed. The results show that the high speed leading—edge rotating cylinder is effective on delaying the flow separation on the upper surface of the airfoil and retarding the boundary—layer development. The proper rotating speed ratio for the cylinder is around 4 and the appropriate gap distance is a—bout 2.5mm to 1.5mm.Moreover,results suggest that,integrated with the high speed leading—edge and trailing—edge rotating cylinders,the aerodynamic performances of the symmetrical airfoil with simple flap can be comparative to those careful designed multi—element airfoils.