According to the requirements of a large amphibian's operating features and performance based on the original wing

a high-lift device design technology of boundary layer control jet flap was studied.The scheme of boundary layer control jet flap was designed. By using computational fluid dynamics numerical simulation as a means to assess the preliminary design

the design scheme's aerodynamic characteristics and flow field structure were analysed and evaluated

and finally wind tunnel tests were conducted to verify the lift effect of the scheme.The result of the design scheme showed that in a wide range of blowing momentum coefficient

the maximum lift coefficient had varying degrees of growth; when the blowing momentum coefficient was 0.2

the incremental maximum lift coefficient was 1.0; according to the influence of the prototype slipstream projections

when the boundary layer control jet flap was employed

the take off and landing speed could drop about 30%

achieving the design target.