METHOD TO PROTECT AIRCRAFT WING LEADING EDGE AGAINST ICING AND AIRCRAFT EXPLOITING THIS METHOD

摘要

FIELD: aircraft engineering.;SUBSTANCE: method to protect hollow leading edge (1) of aircraft wing (2) against destructive effects of superhigh temperatures of hit air (f) used to fight against icing and circulated inside said hollow leading edge (1). Said front edge has its rear covered by baffle (3) jointing together leading edge upper surface (1E) and lower surface (1I). Hot air (f) used to fight against icing is bled from engine (M). Fluid medium flow (EF) on one of leading edge surfaces (1E, 1I), ahead of said baffle, is acted upon so that said flow is acted upon to make it change from laminar state (EFL) into turbulent stet (EFT). Aircraft is distinguished for by hot air feed from engine to wing leading edge (1) of aircraft wing (2).;EFFECT: intensified heat exchange and minimised thermal strains on leading edge.;8 cl, 2 dwg