Abstract: Based on computation and windtunnel test, a rational aerodynamic configuration ofsheared wingtip is posed, including optimum design of planform and airfoil, and the higher demands of increased lift and reduced drag at cruise and in climb are met. A method combining both the panelvo rtexlat tice method and the suction analogy method of the vo rtexlift distribution in the span direction is adopted, which may account for the nonlinear aerodynamics and raise the calculation precision and speed. The computation and experimental data are in fair agreement. After analyses, it is obtained that a sheared w ingtip with highly leadingedge sweptangle, mounted on the tip of a rectangular wing, can make the spanwise circula ion distribution of the wing close to anellip tical distribution, and the leadingedge separated vortex on the sheared w ingt ip mayrest rain the trailing vortex on the wing tip ( to cause the trailing vortex st rength to drop ) , and may produce additional lift on the sheared wing tip.

Key words: nonequilibrium flow, wings, aerodynamic coefficients, exponential functions