Patent Document ID: 20140343905
Application ID: 13985045
Patent Flag: 0

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