Pitching airfoils with Co-Flow Jet (CFJ) flow control are simulated using Unsteady Reynolds Average Navier-Stokes (URANS) at Mach number 0.4 with reduced frequency of 0.1. The flow is transonic with shock wave boundary layer interaction. A 5th order WENO scheme for the inviscid flux, a 4th order central differencing model for the viscous terms and the one equation Spalart- Allmaras model for the turbulence are used to resolve the flow. The airfoil oscillate around its mean AoA of 10° with amplitude of 5°, 7.5° and 10°. The study demonstrates that the CFJ pitching airfoil is very effective to remove dynamic stall at high Mach number of 0.4. The performance is significantly enhanced with radically increased lift, reduced drag, and decreased moment variation.