Simulation of aircraft wake vortex using pressure-based unified numerical approach for incompressible and compressible flows

A wake vortex simulation using CFD methodology based on a new pressure-based unified approach is presented. A numerical method is developed to attain calculation for both in incompressible and compressible flows regime with a low numerical diffusive property and for high prediction accuracy of pressure gradient. This scheme is constructed by splitting the full Navier-Stokes equation into an advection role by velocity and a propagation role by acoustic wave. In the advection phase, concept of the advective upwind splitting method (AUSM) is adapted to non-conservative advection equations. For the acoustic phase, SMAC-like Poisson's equation is derived to reduce a numerical error. Newly developed scheme shows good agreement except strong shock capturing capability for validation problems including incompressible, compressible and vortical flow calculations. Finally, wake vortex simulation for NACA0012 rectangular wing is investigated. The computation results show availability of new approach for wake vortex flow predictions.