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针对跨声速条件下,小展弦比截尖三角翼尾舵的旋成体导弹在小迎角、零侧滑、大舵偏对称状态下呈现出的非对称流动现象,本文首次对其进行了分析研究。首先,通过一系列测力试验、表面油流试验及粒子图像测速(PIV)试验对该非对称流动现象进行了精准捕捉,并对其产生的原因进行了分析。然后,基于已获得的试验数据及流场观测结果,借助数值模拟方法对所述非对称流动的细节、拓扑结构、空间形态及舵面压力分布等问题做了深入研究,并进行了详细讨论。结果表明:旋成体导弹小展弦比舵面大偏度对称偏转时,舵面前缘产生的翼尖涡会因舵面相距较近而相互干扰,促使翼尖涡沿流向非对称发展,使得舵面压力分布不均,最终导致非对称流动和较大横向量的产生,影响导弹的气动性能。
Aiming at the asymmetric flow phenomenon of the small body-to-body ratio spin-body missile with the delta wing tail rudder transversally symmetrical at low angle of attack, zero side slip and large rudder under the transonic condition, this paper analyzes it for the first time the study. First of all, this asymmetric flow was accurately captured by a series of force test, surface oil flow test and particle image velocimetry (PIV) test, and the causes of the asymmetric flow were analyzed. Then, based on the obtained experimental data and flow field observations, the details of the asymmetric flow, topological structure, spatial morphology and pressure distribution on the rudder surface are numerically studied and discussed in detail. The results show that the wing tip vortex generated at the front edge of the rudder can interfere with each other due to the small eddy ratio of the small aspect ratio of the rudder missile, which causes the tip vortex to develop asymmetrically along the flow direction, Surface pressure distribution is uneven, eventually leading to asymmetric flow and large transverse amount of production, affecting the aerodynamic performance of missiles.