Abstract: Massive parallel computational fluid dynamics is a vital tool for modern aviation industry. The parallel aerodynamics numerical simulation techniques based on unstructured mixed grid and cell-centered finite volume method (FVM) were presented in this paper. These techniques were developed for complicated configurations in industrial applications. The algorithms were discussed in detail for parallel implementation with message passing interface (MPI), including compact numerical discrete schemes, grid partition methods for multi-processors based on Metis software package, ghost cells method for both physical and parallel boundary faces, and data transfer scheme. The parallel computing was verified by using a revolving model of relatively small amount of grid cells, and the convergence characteristics of aerodynamic force and flow variables residual were discussed. A large transport airplane configuration with about a hundred millions of grid elements was used for parallel test. An excellent performance of speed up was obtained, and the efficiency was above 80% with up to 18816 processors.