Patent Document ID: 9390205
Application ID: 13985045
Patent Flag: 1

Claim One:
1. A computer implemented numerical method, vorticity-refinement, for simulating aircraft wing-tip vortex flows, said vorticity: refinement includes the following steps: (1) dividing an original vorticity confinement into two parts, {right arrow over (B)} 1 and {right arrow over (B)} 2 , and moving {right arrow over (B)} 1 into left hand side of momentum equation of incompressible flows; (2) transferring the {right arrow over (B)} 1 into flux on interfaces of computing cells by utilizing a Gaussian theorem and discretizing the flux by using high-order spatial discretization schemes; (3) keeping the {right arrow over (B)} 2 in a source term position of the momentum equation of incompressible flows; (4) simulating the wing-tip vortex of an aircraft, on a computer, utilizing two different factors ε 1 and ε 2 in {right arrow over (B)} 1 and {right arrow over (B)} 2 , refining added vorticity and forming the vorticity refinement process of the simulation; and (5) generating a graphical representation of the wing-tip vortex based on the simulation of the wing-tip vortex of the aircraft.