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本文重点介绍了在机头周向角±45°处的颗粒微扰动对战斗机大迎角航向气动特性的影响进行了数值模拟研究。结果表明:在机头周向角±45°处的颗粒对大迎角下飞机的航向气动特性影响明显,能够使大迎角偏航力矩具有确定的方向。对流场结构分析发现:颗粒所在一侧脱离出明显强于没有颗粒一侧的小涡,从而在机头该侧诱导出更强的分离涡,进而导致了飞机大迎角非对称气动力的出现。
This article focuses on the numerical simulation of the effects of particle perturbations at ± 45 ° of the nose circumference on the heading aerodynamic characteristics of fighter aircraft at high angles of attack. The results show that the particles at ± 45 ° of the nose circumference have an obvious influence on the aerodynamic characteristics of the aircraft at high angles of attack, and the yaw moment at high angles of attack can have a definite direction. The analysis of the structure of the flow field shows that the side where the particle is located is separated from the small vortex which is obviously stronger than the non-particle side, which induces a stronger separation vortex on the side of the nose and leads to the asymmetric aerodynamic appear.