Vorticity-refinement based numerical method for simulating aircraft wing-tip vortex flows

摘要

The present invention relates a numerical method to simulate the incompressible wing-tip vortex flows. This method is called Vorticity-Refinement, which refines the added vorticity as two different forms of force multiplied by two different factors to counteract the numerical diffusions in the numerical solutions by utilizing the high-order spatial discretization and improving the stability and convergence of the governing equations for incompressible flows.

主权项

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 ε1 and ε2 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.