Three-dimensional computations are performed for steady and unsteady transonic flows over a F-5 wing using a parallel implicit solver. The numerical scheme is based on a cell-centered finite-volume method with implicit Gauss-Seidel time integration and Roe`s flux-difference splitting. For parallel computation, local sub-domains are decomposed using MeTis library considering the balance of the number of cells. Parallel implementation is made using MPI library. Steady computation of a F-5 wing is performed to validate the capability of parallel computation. A case of an oscillating F-5 wing is also compared with experimental data for the validation of time accurate computations.