The forced vibration of the 2D NASA flutter compressor cascade is numerically simulated in full scale with parallel computation technique. The compressor cascade consists of 9 blades bounded by 2 wind tunnel side walls. The implicit line Gauss-Seidel iteration with dual time stepping is employed. The turbulence is modeled with the Baldwin-Lomax model. A newly developed high resolution efficient scheme, Zha-CUSP2 scheme, is applied to compute the inviscid flux. The blades vibrate with a constant inter blade phase angle of 180 degree. The numerical simulation is carried out at a zero degree incidence with reduced frequencies of 0.4, 0.8 and 1.2. The computed unsteady pressure, aerodynamic moment and the local stability are compared with the experiment measurement.