Provided is a method for designing a wind
turbine blunt
trailing edge oval
wing section. The semi-major axis, the semi-
minor axis and the primary
wing section rear
trailing edge section of a primary
wing section are determined through a dimensionless geometric equation of the primary wing section; the
trailing edge of the primary wing section is
cut off, and the trailing edge of the blunt trailingedge oval wing section is obtained; and the portion between the
leading edge and the trailing edge section of the primary wing section is the blunt trailing edge oval wing section. According to the method, aiming at the defects of an existing large-thickness wind
turbine wing section design method, the characteristic that the larger the
relative thickness of the oval wing section is, the larger the stalling
attack angle is and the advantages of a bunt trailing edge improving method are combined, the wing section cross sectional
moment of inertia is 50% larger than the cross sectional
moment of inertia of a large-thickness blunt trailing edge wind
turbine wing section FX77 with the same chord length, the pressure gradient of the wing section
suction surface rear section is 25% smaller thanthat of an FX77
suction surface rear section, the lift coefficient and stalling
attack angle of the wing section are effectively increased, and the strength and rigidity of wind turbine blades are improved.