双垂尾不利影响改善措施研究  

A study on the measures to cut down twin-tails' unfavorable influences

作　　者：郑遂[1,2] 李桂生[2] 蔡广平[2] 昂海松[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]成都飞机设计研究所,成都610041

出　　处：《实验流体力学》2012年第1期66-69,共4页Journal of Experiments in Fluid Mechanics

摘　　要：采用一个典型的双垂尾鸭式布局模型,利用CFD手段对垂尾导致大迎角升力减小现象的机理进行了研究。发现在低速大迎角条件下,前体脱体涡在机身后体诱导出向外的速度分量,致使垂尾处于'侧滑'气流中,增大了垂尾内侧压力,与此伴生的逆压梯度,削弱了前体涡强度和稳定性,从而使飞机升力减小。根据这一发现,设计了减小垂尾面积、垂尾前缘内偏和变化外倾角3种改善措施。通过风洞试验验证,减小垂尾面积和垂尾前缘内偏具有明显的改善大迎角升力特性的效果。The research was done on a typical canard configuration with twin-tails to find why tails always reduce the lift at high angle-of-attack by using CFD method.It was found that the vortices passing above induced a ＂sideslip＂ flow field in the region tails located.The tails thus had higher pressure on the inboard side which put an adverse pressure gradient in the field.It was this gradient to weaken and destabilize the vortices and then to reduce the vortex lift on the whole model.Based on the findings,three improving measures were designed,which were small size vertical tails,toe-in vertical tails and different tail incline angles.The wind tunnel test results showed that the first two received expected effects.

关 键 词：边条翼布局 双垂尾 前体涡 大迎角 升力 

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]