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大型飞机常采用开启襟翼以增大机翼升力系数,实现较大迎角的起飞和降落,而机翼在大迎角状态下,翼尖会产生能量集中且自由消散时间长的飞机尾涡,严重影响后续起降飞机的安全。基于Rayleigh-Ludwieg不稳定性,提出一种新概念飞机襟翼布局,通过水槽实验发现:新概念布局的襟翼对翼尖涡的消散具有明显的促进作用,不同参数组合下襟翼涡对翼尖涡的运动特性和能量变化的影响均有不同。实验结果也为飞机尾流控制的研究提供了参考,在满足飞行力学设计的基础上,合理运用增升装置构建四涡系统可以有效促进飞机尾流的消散,提高机场飞机起降效率。
Large aircraft often use open flaps to increase the wing lift coefficient, to achieve a larger angle of attack of the take-off and landing, and wings at high angles of attack state, the tip will produce a concentrated energy and dissipate a long time tail vortex , Seriously affecting the safety of subsequent take-off and landing aircraft. Based on the Rayleigh-Ludwieg instability, a new concept of aircraft flap layout is proposed. The experimental results show that the flaps of the new concept layout can obviously promote the dissipation of the wingtip vortex, and the wing vortex-wing Vortex motions and energy changes have different effects. The experimental results also provide a reference for the research of aircraft wake control. Based on the design of flight mechanics, the rational use of the lifting device to build a four-scroll system can effectively promote the dissipation of aircraft wake and improve the take-off and landing efficiency of the aircraft.