摘要
机翼前缘结冰会改变机翼的气动轮廓并影响整体的空气动力学性能.研究简化角冰冰形对翼型绕流流场结构的影响可以为飞机防冰设计提供有价值的参考.采用粒子图像测速技术,在低速直流风洞中对覆盖不同角冰冰形的翼型在不同攻角时的流场结构进行了详细的实验测量.实验对象包括三种简化的冰形和原始冰形.结果表明,在本研究范围内,覆盖简化冰形的翼型和覆盖原始冰形的翼型在流场参数上的最大差异为35.11%.与原始冰形相比,覆盖简化的角冰冰形的翼型流场中的分离泡距离翼型前缘和后缘更远.在三种冰形简化方法中,将冰角简化成矩形并在冰角之间添加抛物线的连接方式具有比较好的简化效果.在选定的两个区域中,这种简化冰形和原始冰形在翼型绕流流场的参数平均值的差异在14.88%之内.
Ice can change the leading-edge profile of the airfoil and affect the overall aerodynamic performance of the airfoil.Studying the effects of simplified horn ice shapes on the flow field structures can provide a valuable reference for aircraft anti-icing/deicing design.Detailed experimental measurements of the flow field structures of the airfoil with different horn ice shapes were carried out in a low-speed direct wind tunnel using the particle image velocimetry technique.Three simplified ice shapes and the original ice shape were tested at different angles of attack.The results showed that,within the scope of the present study,there was a maximum 35.11%difference in the flow field parameters between the airfoil with simplified ice shapes and the airfoil with the original ice shape.Compared with the original ice shape case,the separation bubbles of the simplified ice shape cases were farther away from the leading edge and trailing edge of the airfoil.Among the three ice shape simplification methods,adding connecting lines between rectangular ice tips was found to have the optimum simplification effects in the flow structures and the airfoil performances.Using this simplification method,the maximum flow field differences at various angles of attack were within 14.88% in the selected two regions.
作者
郑诚毅
金哲岩
杜旭之
东乔天
杨志刚
Chengyi Zheng;Zheyan Jin;Xuzhi Du;Qiaotian Dong;Zhigang Yang(School of Aerospace Engineering and Applied Mechanics,Tongji Universiy,Shanghai 200092,China;Shanghai Key Lab of Vehicle Aerodynamics and Vehicle Thermal Management Systems,Shanghai 201804,China;Department of Mechanical Science and Engineering,Universiy of Ilinois,Urbana 61801,USA;COMAC Shanghai Aircraft Design&Research Institute,Shanghai 201203,China)
基金
This work was supported by the National Natural Science Foundation of China(Grant No.12372279)
the National Engineering Research Center of New Energy Vehicles and Power Systems
the Shenyang Key Laboratory of Aircraft Icing and Ice Protection。
