鸭式布局飞行器的翼体摇滚特性风洞试验

Wind tunnel test for wing-body rock of canard-configuration aircraft

为研究鸭式布局飞行器摇滚特性,设计了一种包括鸭翼、脊型前体、边条翼、主翼和垂尾的模型,进行了自由滚转、扰动滚转、静动态测力和烟线流场显示多种技术手段相结合的风洞试验。通过自由滚转和扰动滚转试验得到了该模型翼体摇滚的时间历程,静态测力和动导数测定验证了非极限环运动形式摇滚的发生。结果表明该鸭式布局模型摇滚不仅同侧存在多个摇滚平衡点,而且在临界俯仰角,摇滚过程中可能出现从一摇滚平衡点跳动至同侧另一摇滚平衡点的突变。通过流场显示技术得到该鸭式布局模型复杂流场的基本形态分布,并对滚转角为0°时的全机涡系干扰和摇滚形成机理进行了简要分析。

In order to study wing-body rock of the canard-configuration aircraft,different methods including free rolling motion,applying disturbance to free rolling motion,static force balance test,dynamic derivative test and smoke wire technique are used for the model which has canard wing,chine forebody,strake wings,main wings and a vertical fin in the wind tunnel.The roll angle time history is obtained by free rolling motion and disturbed motion,and then non-limit cycle motion is verified by static force balance test and dynamic derivative test.The results show that rolling motions of the canard-configuration aircraft model have several different central angles in the same side,and one center can jump to the other at the critical pitch angles.Finally,the basic flow field distribution of the canard-configuration aircraft model is described by flow visualization technique.The vortex system interaction mechanism and cause of wing-body rock of model are briefly analyzed at 0°rock angle.