The invention discloses a low-resistance laminar flow airfoil profile applied to a high-altitude high-speed long-endurance unmanned aerial vehicle and relates to the technical field of aerospace. An airfoil profile has the maximum thickness of 12.22% cA at the maximum thickness position of 39.13% cA, the maximum camber of 2.09% cA, the maximum camber position of 59.1% cA and the leading edge radius of 0.76% cA, and cA is the chord length of the airfoil profile. According to the invention, the airfoil profile with better robustness is designed according to the surface curvature change and the pressure distribution of the airfoil profile, wherein the airfoil profile can achieve a high altitude of more than 18000m; the relatively long laminar flow area is ensured by utilizing the relatively small curvature change of the upper surface of the airfoil; through the design of the weak reverse pressure gradient section, trailing edge flow separation is avoided, the pressure distribution robustness is good, the airfoil profile resistance is lower, the lift-drag ratio is higher, the resistance divergence Mach number is large, the airfoil profile performance is good, and the requirements of high-altitude, high-speed and long-endurance unmanned aerial vehicles can be completely met.
本发明公开了一种应用于高空高速长航时无人机的低阻层流翼型,涉及航空航天技术领域,所述翼型的最大厚度为12.22%c,最大厚度位置为39.13%c,最大弯度为2.09%c,最大弯度位置为59.1%c,前缘半径为0.76%c,其中c为翼型弦长。本发明根据翼型表面曲率变化和压力分布设计出了能够实现18000m以上高空具有更好的鲁棒性的翼型,在利用翼型上表面较小曲率变化保证层流区域较长的同时,通过弱逆压梯度段的设计避免了后缘流动分离,使其压力分布稳健性较好,翼型阻力更低、升阻比更高、阻力发散马赫数较大,翼型性能较好,可以完全满足高空高速长航时无人机的需求。
Low-resistance laminar flow airfoil applied to high-altitude high-speed long-endurance unmanned aerial vehicle
一种应用于高空高速长航时无人机的低阻层流翼型
2020-08-07
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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