The invention belongs to the field of aircraft pneumatic layout design, and relates to a rising wingtip design method. The method comprises the steps of: building a vorticity calculating method for reducing the wingtip vortex streaming by using the wingtip reverse streaming vortex; designing a rising wingtip to partially counteract the circular reactor of the wingtip vortex to reduce the loss of wingtip three-dimensional streaming so as to achieve the purposes of reducing the whole aircraft resistance and improving the whole aircraft lift; calculating the position and the feature size of a space-inclined curved surface through the fluid mechanics to perform optimal adjustment and selection; and further performing the verification and the optimization for the design through a wind tunnel test. The rising wingtip design method creatively builds the resistance-reducing and lift-improving design principle of the wingtip reverse streaming vortex, and initiates the rising wingtip design principle and method capable of improving the lift while reducing the structural weight and simplifying the structural design.