Universal laminar flow airfoil suitable for medium-low speed unmanned aerial vehicle

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％。