摘要
针对某型大展弦比飞机由于外翼的当地雷诺数降低以及翼面展向流动,中外翼提前内翼发生分离,引起升力系数下降以及横向滚转力矩发散的情况,基于涡流发生器可以对附面层注入能量的理论,我们在大展弦比飞机的中外翼布置涡流发生器,计算分析了涡流发生器布置在缝翼下表面、缝翼上表面以及主翼面引起的流动的影响,并且在低速高雷诺数风洞中进行了涡流发生器的位置、高度、偏度以及数量的研究。研究结果表明:缝翼上表面和下表面的涡流发生器未能减弱缝翼和主翼的分离;主翼面的涡流发生器减弱了主翼的分离,将最大升力系数提高0.05,推迟滚转力矩发散1°~2°。
Aiming at the situation of a large aspect ratio aircraft due to the lower local Reynolds number of the outer wing and the span-wise flow of the wing surface,the middle and outer wings separation before the inner wing,which causes the lift coefficient to drop and the lateral roll moment to diverge.Based on the theory that the vortex generator can inject energy into the boundary layer,the vortex generator is arranged in the outer wing of a large aspect ratio aircraft.The influence of the flow caused by the arrangement of the vortex generator on the lower surface of the slat,the upper surface of the slat and the main wing surface is calculated and analyzed.The position,height,angle and quantity of the vortex generator are studied in the low-speed and high-Reynolds number wind tunnel.The research results show that the vortex generators on the upper and lower surfaces of the slat fail to weaken the separation at the slat and the main wing;the vortex generators on the main wing surface weaken the separation of the main wing,increase the maximum lift coefficient by 0.05,and delay the roll moment divergence by 1°—2°.
作者
周星
钟园
ZHOU Xing;ZHONG Yuan(Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Ltd., Shanghai 201210, China)
出处
《复旦学报（自然科学版）》
CAS
CSCD
北大核心
2022年第1期10-16,共7页
Journal of Fudan University：Natural Science
