编队飞行风洞实验研究

发布时间：2018-01-08 16:01

本文关键词：编队飞行风洞实验研究　出处：《实验流体力学》2016年04期 　论文类型：期刊论文

【摘要】：在1m非定常风洞中开展了两机编队飞行试验研究。前机采用尾支撑转接垂直叶型支杆与坐标架连接,可以实现相对位置(纵向、侧向和垂向间距)的精确改变;后机通过尾支撑连接到风洞的主支撑机构上,可以实现迎角的变化。采用内式六分量应变天平测量后机的气动力受前机尾涡流影响的变化情况,对后机的绕流场进行了PIV测量。试验中使用了2组模型,一组是简化的翼身组合体模型,另一组是翼身融合体飞翼布局模型。结果表明:当前机翼尖涡靠近后机翼面时,后机的升阻比变化较明显;当前机翼尖涡靠近后机翼尖时,后机可获得最大升阻比;前机迎角增大时,后机的升阻特性有较明显变化;当后机的迎角大于8°时,其升阻比基本不受前机影响。
[Abstract]:The formation flight test of two aircraft was carried out in a 1m unsteady wind tunnel. The front aircraft was connected with the coordinate frame by the tail support and the vertical blade supporting rod, and the relative position could be realized (longitudinal). The exact change of lateral and vertical spacing; The rear machine is connected to the main supporting mechanism of the wind tunnel through the tail support, which can realize the change of the angle of attack. The change of the aerodynamic force affected by the eddy current at the front end of the wind tunnel can be measured by the internal six-component strain balance. The flow field around the rear machine was measured by PIV. Two groups of models were used in the experiment, one of which was a simplified wing body model. The other group is the wing body fusion wing layout model. The results show that when the tip vortex of the wing is near the rear wing surface, the lift-to-drag ratio of the rear wing changes more obviously. The maximum lift-to-drag ratio can be obtained when the current tip vortex of the wing is close to the tip of the rear wing. When the angle of attack of the front machine increases, the lift resistance characteristic of the rear machine changes obviously. When the angle of attack of the rear engine is greater than 8 掳, the ratio of lift to drag is almost unaffected by the front machine.
【作者单位】：中国科学技术大学工程科学学院;中国空气动力研究与发展中心;南京航空航天大学航空宇航学院;
【分类号】：V211.74
【正文快照】： 0引言编队飞行是指2架或2架以上飞机按一定队形编组或排列飞行。各机之间必须保持规定的距离、间隔和高度差。基本的编队队形有Λ队、梯队等。编队的中心问题是保持规定队形并充分发挥飞机性能。编队飞行需要在对飞机尾涡有深入的了解、准确的相对位置测量和良好的飞行控制方

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