AIRFOIL OF THE CARRIER ELEMENT OF AN AERIAL VEHICLE Russian patent published in 2023 - IPC B64C11/18 B64C27/467 

FIELD: aviation.

SUBSTANCE: invention relates to aviation and can be used in designing main and tail rotor blades of rotary-wing aerial vehicles. Airfoil of the carrier element of an aerial vehicle, formed by the upper and lower parts of the contour thereof, provided with a rounded leading edge, a pointed or blunted trailing edge, interconnected by the smooth upper and lower sections of the airfoil contour. Herewith, the distance Yv measured from the airfoil chord along the normal thereto up to the upper part of the contour gradually increases from the leading edge of the airfoil to the maximum value thereof Yv_max 0.0778B in the range X 0.36B…0.37B. The rounded leading edge of the airfoil is made with a radius of curvature Rv along the upper part of the contour equal to Rv=0.019B, wherein said radius then gradually increases along the airfoil chord up to values Rv=1.9B, at the point of the contour farthermost from the airfoil chord, wherein X is the distance counted from the leading edge along the airfoil chord, B is the airfoil chord. The distance from the airfoil chord to the contour thereof decreases monotonously in the direction of the trailing edge, and the radius of curvature of the upper part of the contour continues to increase up to the value of 0.85B, wherein the convex front part of the contour of the upper airfoil surface is smoothly mated with the rectilinear tail section. The angle between the tangent to the upper part of the contour and the airfoil chord at X=B is 10.35°. The distance Yn measured from the airfoil chord along the normal thereto down to the lower part of the contour gradually increases from the leading edge of the airfoil up to the maximum value thereof Yn_max 0.0366B at X=0.26B and then decreases monotonously to the trailing edge of the airfoil. The rounded leading edge of the lower airfoil surface is made with a radius of curvature Rn=0.0127 B along the lower part of the contour, increasing non-monotonously along the airfoil chord, reaching the maximum at X=0.675B, and then decreases down to values of 1.0B…1.2B at the trailing edge at X=B; the angle between the tangent to the lower part of the airfoil contour by the trailing edge and the airfoil chord is 5.4°, and the thickness of the trailing edge of the airfoil is 0.005B.

EFFECT: higher aerodynamic quality as compared with the prototype NACA 23012 at higher values of the lift coefficient Cya at Mach numbers M=0.5 to 0.8.

4 cl, 12 dwg, 2 tbl