The numerical simulation of the aerodynamic characteristics influences for civil wing-mounted jet exhausts were presented. Three-dimensional time-dependent compressible Reynolds-averaged Navier-Stokes equations were solved with third-order upwind-biased flux-difference splitting method and approximate factorization method. The point-to-point patched multi-block technology was used to generate high quality grid. The multi-grid technique was employed to accelerate the convergence. For a better simulation of the power effects, the fan inlet face boundary conditions and jet-exit boundary conditions were determined. Computational results and comparisons with experimental data are presented. The good agreement indicates that the numerical methods are validated. From the results, lift and moment characteristics are influenced by jet exhausts certainly.
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