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为了研究鸭式布局飞机的摇滚运动,设计了一种包括鸭翼、脊型前体、边条翼、主翼和垂尾的模型,进行滚转自由度释放、静态测力、动导数试验和烟线流场显示多种技术手段相结合的风洞试验。首先为了得到摇滚从发生到消失的全过程,进行了俯仰角范围为12°~52°、间隔1°测量的滚转自由度释放试验;结果表明对应于不同的俯仰角,鸭翼布局飞机的摇滚运动也具有不同的性质,其平衡点和运动形式均发生变化。接着静态测力和动导数试验证实:在翼体结构的多涡系影响下,摇滚可在零度平衡点和非零平衡点位置处发生;且运动可为极限环和非极限环形式。最后通过流场显示,分析了在不同迎角时鸭式布局飞机形成翼体摇滚的可能的流动机理。
In order to study the rocking motion of a duck-shaped aircraft, a model of duck wing, ridge precursor, wing wing, main wing and vertical tail was designed to study the release of roll freedom, static force measurement, dynamic derivative test and smoke The line flow field shows a combination of wind tunnel tests with various technical means. First of all, in order to get the whole process of rock from occurrence to disappearance, the free-wheeling degree of freedom test was carried out with the range of pitch angle of 12 ° ~ 52 ° and the interval of 1 °. The results show that for different pitching angles, Rock movements also have different properties, with changes in balance and movement patterns. Then the static force measurement and the dynamic derivative test confirm that the rock can occur at the zero-equilibrium point and the non-zero equilibrium point under the influence of the multi-vortex structure of the wing structure, and the motion can be in the form of the limit ring and the non-limit ring. Finally, through the flow field display, the possible flow mechanism of the wing-body rock formation by the duck-type aircraft at different angles of attack is analyzed.