The flow-fields around powered isolated turbofan engine model and powered DLR-F6 wing/body/pylon/nacelle(WBPN) model were numerically simulated and analyzed by the appropriate fan inlet face and jet-exit boundary conditions.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 powered effects

the fan inlet face boundary conditions and jet-exit boundary conditions were determined.Computational results and comparisons with experimental data were presented.The good agreement indicates that the numerical method

grid blocking strategy and management of boundary conditions are validated.