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为解决飞翼布局起降状态俯仰控制能力不足问题,研究一种新型的腹部扰流板俯仰控制装置。针对带地效翼型,采用数值计算方法,研究了扰流板高度、弦向位置、偏度、迎角、离地高度等参数对俯仰与升阻性能的影响及其流动机理,给出了扰流板设计原则。研究结果表明,在地效作用下,合适的扰流板弦向位置和高度与偏度配合,可提供显著的抬头力矩增量和较大的升力增量,有助于提高飞机起降性能。针对附加的较大阻力增量,扰流板面开孔影响探索性研究表明,开孔可减小附加阻力,提高升阻比,但使抬头力矩增量有所减小。扰流板是一种改善无尾飞翼布局俯仰操纵的有效措施,值得深入研究。
In order to solve the problem of lacking of pitch control ability of takeoff and landing in the flying wing layout, a new type of abdominal spoiler pitch control device is studied. Aiming at the airfoil with ground effect, the effects of spoiler height, chordwise position, skewness, angle of attack and ground clearance on the pitch and lift properties and the flow mechanism are studied numerically. Spoiler design principles. The results show that the suitable spoiler chordal position and height and skewness under ground effect can provide notable head-up moment increment and large lift increment, which helps to improve the take-off and landing performance of the aircraft. In view of the additional large resistance increment, the influence of spoiler surface opening exploratory research shows that the opening can reduce the additional resistance, improve the lift resistance ratio, but make the head torque increment is reduced. The spoiler is an effective measure to improve the pitch control of the tailless wing layout, which deserves further study.