Abstract:

An N S method for solving the flow around a wing with deflection of control surface (aileron) is presented. Using the combination of patched grid and domain decomposition techniques, the complex flow around this kind of configuration is effectively solved. An internal coupling condition satisfying the conservation of flux is given. In the computation, van Leer's scheme is used to discretize the inviscid flux terms and a new limiter function is constructed to realize TVD character. The viscous flux terms are discretized by using a central difference scheme. Numerical results show that the present method is effective for solving the flow around a wing with control surface deflection.

Key words: N-S equat ions, domain decompo sit ion method, flow w ith cont ro l surface deflect ion