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为了提高飞机在着陆过程中的气动性能,提出了一种新方法:将翼型上翼面的一段表面设计为活动部分。当飞机进入着陆阶段的较大迎角时,通过活动部分在上翼面形成一个台阶产生稳定的驻涡,再联合Gurney襟翼,达到同时提高翼型的升力、失速迎角及增加翼型阻力的目的。在NACA2415翼型上对上述方法进行了验证。结果表明,翼型最大升力系数从原始翼型的1.548 232提高到2.160 687,最大升力系数所对应的迎角可以从原始翼型的17°提高到20°。可见,所提出的新方法对提高飞机的着陆性能是有效的。
In order to improve the aerodynamic performance of aircraft during landing, a new method is proposed: a section of the upper airfoil surface is designed as a moving part. When the aircraft enters the landing phase of a larger angle of attack, through the active part of the formation of a step in the upper airfoil stable vortices, combined with Gurney flaps, while improving the airfoil lift, stall angle of attack and increase airfoil resistance the goal of. The above method was verified on the NACA 2415 airfoil. The results show that the maximum lift coefficient of the airfoil increases from 1.548 232 to 2.160 687, and the angle of attack of the maximum lift coefficient can be increased from 17 ° to 20 ° of the original airfoil. As can be seen, the proposed new method is effective in improving the landing performance of the aircraft.