This paper presents the development of a 3-D parallel flow solver for turbulent flows around rotating bodies using unstructured grids. Cell centered finite volume solver which employs Roe's upwind flux differencing scheme, Spalart-Allmaras turbulence model and Runge-Kutta explicit multistage time stepping scheme is presented. Arbitrary Lagrangian Eulerian (ALE) formulation is implemented for moving grids. The computational grid is partitioned by METIS and PVM is used for inter-process communication. The main objective of this study is to be able to solve unsteady turbulent flows around rotating missile configurations and to evaluate the aerodynamic stability derivative coefficients. Solutions over a non-spinning and spinning M910 projectile configuration are presented. Aerodynamic stability derivative coefficients obtained are found to be qualitatively in agreement with the analytical solutions, experimental data and published numerical solutions.