Abstract
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. fiy 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 X IO6 and a = 20 deg. Numerical results indicate that the first-order-accurate scheme is unable to capture the wing vortex, while the second-brder-accurate scheme has successfully simulated the vortical interaction between the strake and wing vortices.
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