A second order accurate, both in time and space, scheme is developed and implemented for the solution of time dependent Navier-Stokes equations envolving high Reynolds number flows. The numerical results indicate that, even with coarse grids and large time steps, the details of the flow fields are depicted properly concerning the recirculation and wake regions. As a test case uniform flow past a sphere at Re = 162 000 is studied. The surface pressure distribution obtained, compares well with the experimental data, whereas the drag coefficient is slightly underestimated. The turbulent flow past a sphere at a super critical Reynolds number is also analized. The total drag coefficient agrees well with the experimental value at a Reynolds number of 424 500. Finally, with the developed code, the flow past a helicopter fusalage is analized. Flow separation due to cross sectional area reduction and the wake behind the fusalage are resolved accurately.