Computation of vortical interaction for a sharp-edged double-delta wing

An implicit finite-difference scheme is used to compute the three-dimensional incompressible laminar vortical flow around a sharp-edged double-delta wing with an aspect ratio of 2.06. By adding a time derivative of the pressure to the continuity equation, the unsteady incompressible Navier-Stokes equations can be integrated like a conventional parabolic time-dependent system of equations. The flux-difference split scheme combines approximate factorization in crossflow planes with a symmetric planar Gauss-Seidel relaxation in the remaining spatial direction. Up to second-order spatial accuracy is achieved by using an upwind differencing similar to a total variation diminishing scheme. Computations are performed at Re=1.4×106 and α=20 deg.