带背鳍细长平板三角翼脱体涡的实验研究  

Experimental research on the separation vortices over slender delta wing with low dorsal fin

作　　者：贾春[1] 高超[1] 孟宣市[1] 罗时钧[2] 刘锋[2] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]美国加州大学尔湾分校机械与宇航工程系,ca926973975

出　　处：《实验流体力学》2007年第1期46-49,共4页Journal of Experiments in Fluid Mechanics

基　　金：西北工业大学博士创新基金(CX200501)

摘　　要：对后掠角为82．5°具有尖削前缘的细长平板三角翼以及加上背鳍高度分别为hL／s：0．3和hL／s=0．6的机翼组合体在低速风洞进行了大迎角六分力天平测力实验。实验迎角范围为12°-32°，来流速度为25m／s和35m／s。实验结果表明：对单独三角翼，在翼面产生的脱体涡破裂前，其涡流场随着迎角的增大始终是对称且稳定的；增加不同高度的背鳍后，当迎角大到一定程度后，涡流场开始变得不对称和不稳定。背鳍高度不同，流场开始出现不对称时的迎角也不同，在所研究的背鳍高度范围内，背鳍越高，测量得到流场出现不对称时的迎角越小，表明增加低高度的背鳍对细长平板三角翼的背涡流场的稳定有着扰动和破坏作用。实验结果部分证明了文献[1]中的稳定性理论的有效性，同时初步研究了涡失稳后的发展情况。To verify the validity of the theoretical predictions of reference[ 1 ], an experimental research of the high angles of attack is conducted by using a six-component internal strain-gage balance. A sharp-edged flat-plate delta wing of 82.5° sweep angle is tested in a low-speed wind tunnel at angles of attacks up to 32° and sideslip is zero. The same tests are performed on an identical model but with a two low dorsal fin. They are hL/S = 0.3 and hL/s = 0.6.The measurement result of the side-force coefficient clearly indicates that no force asymmetry onset is found for the wing without fin but a force-asymmetry onset occurs over the flat-plate dorsal fin model at zero sideslip. The higher the fin is,the lower the force-asymmetry-onset angle-of-attack is. So the paper provides by the first time direct force-measurement evidence of the theoretical predictions and depicts that the force-asymmetry-onset can be followed by a force-unsteadiness onset.

关 键 词：大迎角 背鳍 非对称力 平板三角翼 涡的稳定性 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]