The invention relates to a universal laminar flow airfoil suitable for a medium-low speed unmanned aerial vehicle. The leading edge radius of the airfoil is 1% C, the maximum thickness of the airfoil is 18.45% C, the maximum thickness position is 40.34% C, the maximum camber of the airfoil is 2.95% C, and the maximum camber position is 57.46% C; wherein C is the chord length. The designed Reynolds number of the airfoil is 2 * 10 < 6 >, but the airfoil has better aerodynamic performance when the Reynolds number is 1 * 10 < 5 >-3 * 10 < 6 >. When the lift coefficient of the airfoil is 0.3-1.2, the resistance coefficient of the airfoil is superior to that of an NLF-0215 airfoil, and when the lift coefficient is designed to be 1.0, the range of a laminar flow area is larger than 60%.
本申请涉及一种适用于中低速无人机的通用层流翼型,翼型的前缘半径1%C,翼型的最大厚度18.45%C,最大厚度位置40.34%C,翼型的最大弯度2.95%C,最大弯度位置57.46%C;其中C为弦长。该翼型设计雷诺数为2×106,但在1×105~3×106雷诺数都有较好的气动性能。该翼型在升力系数0.3~1.2时阻力系数优于NLF‑0215翼型,在设计升力系数为1.0附近层流区域范围超过60%。
Universal laminar flow airfoil suitable for medium-low speed unmanned aerial vehicle
适用于中低速无人机的通用层流翼型
2024-06-14
Patent
Electronic Resource
Chinese
IPC: | B64U |
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