The Euler and Navier-Stokes solutions of a 3-D wing with aileron

The Euler and Navier-Stokes equation for describing complex now phenomena a round a wing with aileron is effectively solved using the combination of do main decomposition technique and patched grids. An internal boundary condit ion satisfied the conservation of flux is given. In computation, Van Leer's scheme and central difference scheme are used for inviscid and viscous flu x terms respectively and a new limiter function is constructed to preserve the scheme having the TVD character. Numerical results show that present me thod is an effective one for describing the flow around a 3-D wing with con trol surfaces.