运输机机翼Kink区域低速特性优化风洞试验研究

Wind Tunnel Test Research On Optimization Of Low-Speed Characteristics in The Kink Area of Transport Aircraft Wings

摘要:

常规布局民用运输机在低速增升构型条件下，失速迎角的提前导致飞机进场速度过大，需要优化高升力构型的低速特性，通过对飞机机翼Kink 区域的流动进行控制来改善飞机的着陆性能。采用风洞试验对发房 外侧导流片和缝翼切角这两种被动控制技术进行研究，获取发房外侧导流片（后缘高度H 中）和缝翼切角（中等切角）的最佳组合方案。结果表明：在最佳组合方案条件下，升力系数明显提升，且俯仰力矩系数在轻微上仰后仍满足经典判据的要求；通过荧光油流试验呈现了优化措施的流动机理，即发房外侧导流片和缝翼切角拖出的携带高能量的旋涡流注入下游机翼表面，抑制了机翼表面的流动分离。

Abstract:

For conventionally laid out civil transport aircraft in low-speed condition and high lift configurations, the advance of the stall angle of attack causes the aircraft"s approach speed to be too high, it is necessary to optimize the low-speed characteristics of the high-lift configuration and improve the landing performance of the aircraft by controlling the flow in the Kink area of the aircraft wing. Wind tunnel tests were used to conduct research on two passive control technologies: nacelle outer strake and slat edge tiny cut, obtained the best combination plan of nacelle outer strake (trailing edge height: H medium) and slat edge tiny cut (medium size cutting), under the best combination conditions, the lift coefficient is significantly improved, and the pitch moment coefficient still meets the requirements of the classic criterion after a slight pitch up. Fluorescent oil flow test reveals flow mechanism of optimized measures, that is, the high-energy vortices generated by nacelle outer strake and slat edge tiny cut are injected into the downstream wing surface, suppressing the separation of the flow on the wing surface.