High-lift-force laminar flow aerofoil profile with low-resistance and high-drag-divergence Mach number

The invention discloses a high-lift-force laminar flow aerofoil profile with a low-resistance and high-drag-divergence Mach number. The radius of a leading edge is 0.025, a maximum camber of 0.031 exists at a 52.8% chord-length position of the airfoil profile, and a maximum thickness of 0.150 exists at a 40.5% chord-length position of the airfoil profile. Because the radius of the leading edge of the aerofoil profile is large, a large favorable pressure gradient is ensured, and the favorable pressure gradient is kept at about 10% of that of the leading edge; the upper surface of the aerofoil profile is in a suitable small-curvature shape, thereby avoiding the rapid recovery of pressure; after the pressure of the leading edge is minimum, in a 20% chord length range, a situation that the pressure distribution pattern has a small adverse pressure gradient is allowed, and the remarkable weak inverse pressure in the section both keeps the stable development of a laminar flow area and facilitates the pressure recovery of a trailing edge, so that an airflow, after being slowed down slowly, enters a stable and linear smooth accelerating process again. The maximum camber position and maximum thickness position of the aerofoil profile relatively stand backwards, so that a situation that a small section of smooth favorable pressure gradient exists behind the weak adverse pressure is ensured, thereby facilitating the continued development of a laminar region, and increasing the lift force.