上仰及小振幅振荡三角翼流动显示研究  

Investigation of flow characteristics of delta wings pitching up and pitching oscillation with small amplitude

作　　者：刘绍辉[1] 张明禄[1] 吕志咏[1] 

机构地区：[1]北京航空航天大学流体力学教育部国家重点实验室,北京100191

出　　处：《实验流体力学》2008年第3期14-17,22,共5页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金(项目号10572014);航空基金(项目号06A51036)

摘　　要：为验证折合频率与无量纲频率对涡破裂点位置的影响,在北航大水洞用动态机构三角翼分别进行了不同折合频率k(k=α.C/2U∞)的上仰-停止运动及不同无量纲n(n=fC/U∞)的小振幅的俯仰振荡实验。实验结果表明,在不同迎角范围上仰时不同折合频率对涡破裂点位置有很大影响,如在破裂涡迎角范围,破裂点随迎角的变化曲线会出现山峰状;对于在破裂涡区作小振幅振荡的三角翼,无量纲频率n对破裂点位置变化也有很大影响。其中,无量纲频率n在1.0左右时为临界值。In order to prove the influnce of the reduced frequency and nondimensional frequency to the location of vortex breakdown, flow visualization tests with a dynamic delta wing have been carried out in a water tunnel of BUAA. Movement types of the delta wing include pitching up in different deduced frequency k （ k = ^＊a C/2 U∞ ） and stopping as well as pitching oscillation with small amplitude in different nondimensional frequency n （ n = fC/U ∞ ） at breakdown vortex regime. In the process from pitching up to stopping the range of angle of attack pitching up has a obvious affect on the variation of vortex breakdown position. When the wing is at pitching oscillation with small amplitude in breakdown vortex regime the nondimensional frequency n has an obvious affect on the breakdown position. It has been shown that nondimensional frequency n = 1.0 is critical frequency.

关 键 词：俯仰 振荡 三角翼 折合频率 涡破裂 流动显示 

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]