FIELD: aeronautical engineering. SUBSTANCE: aerodynamic wing has main part with inverted taper ratio limited by leading edge 30 and two trailing edges 10 running from respective ends of leading edge 30 in direction of point P of rear top and two respective extension 70 in way of wing span in area 50 of laminar boundary layer on wing extending over chord through definite distance from leading edge of above-mentioned wing and from opposite sides of wing in way of span. System of control of laminar flow on sections 60 of wing provides for use of fuel contained in wing as coolant. EFFECT: enhanced efficiency of aircraft wing flaps. 39 cl, 13 dwg
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