微型凸起流动控制用于翼型的减阻特性研究  

Drag Reduction Characteristic Research of Mini-protuberance Flow Control on Airfoil

作　　者：成水燕[1] 聂智军[1] 李立[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2017年第3期40-44,共5页Aeronautical Computing Technique

基　　金：航空科学基金项目资助(2015ZA31002)

摘　　要：微型凸起作为减小阻力的一种有效措施已经备受关注。开展了等熵压缩"弱激波"干扰鼓包用于RAE2822超临界翼型的减阻作用机制研究以及NACA0012对称翼型表面脊状结构减阻特性的数值模拟研究。结果表明:通过鼓包参数最优匹配,可达到弱化激波、减小波阻、提高升阻比、延缓抖振边界等目的;同时,通过对比不同脊状结构、不同网格密度对计算结果的影响,总结了多个速度下脊状表面的减阻规律。所得结论为进一步开展微型凸起类流动控制用于机翼的减阻特性研究奠定了坚实基础。As an effective measure of drag reduction, mini- protuberance has been attracted much atten- tion. In order to develop the study of drag reduction mechanism, the weak shock control bump of quasic- isentropic compression on supercritical airfoil RAE2822 and riblet structure on symmetrical aerofoil NA- CA0012 are numerically investigated by Computational Fluid Dynamics in present paper. The results are as follows： the optimal parameters can weaken shock wave, reduce drag, increase the lift to drag ratio and delay buffet boundary. Meanwhile, By Comparing different riblet structure and mesh density, drag reduc- tion rules of multi- velocity state are summarized. The above conclusions laid a solid foundation for further research on the drag reduction characteristic of wing using mini- protuberance folw control.

关 键 词：微型凸起 流动控制 翼型 减阻 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] O355[理学—流体力学]