A numerical method is presented for calculating the unsteady transonic viscous flows around oscillating aerofoil and wing based on the unsteady Navier-stokes equations.It adopts an implicit NND algorithm and Baldwin-Lomax turbulence model in solving procedure.The computational grid is C and C-H types in a body-fitted coordinate system generated by an algebraical method. The transonic viscous flows around the NACA 0012 aerofoil and M6 wing with pitching oscillation have been calculated.Numerical results are in good agrement with experimental data.