This paper numerically studies the micro-compressor performance with integrated co-flow jet (CFJ) airfoil injection and suction ducts to mimic the wind tunnel testing condition. The simulation is conducted using 3D Reynolds Averaged Navier-Stokes (RANS) solver and the k-ɛ turbulent model. The boundary conditions from the wind tunnel testing are used to simulate the experimental conditions. Five RPMs of the micro-compressor are simulated. The predicted static pressure ratio achieves a very good agreement with the experiment measurements with the maximum discrepancy less than 3%. The results indicate that the micro-compressor is operated at an operating line that is shifted from the design operating line with substantially lower pressure ratio. This is because that the static pressure at the CFJ airfoil injection area near leading edge is very low due to the very strong suction effect caused by the CFJ injection effect. Working at the off-design condition decreases the compressor efficiency from the designed value of 80% to about 25%. This off-design operation is because the CFJ airfoil with the injection/suction ducts and the micro-compressors are designed with a loose integration, which creates the mismatch between the compressor provided back pressure and the static pressure required by the CFJ injection duct outlet. The micro-compressor is over-designed to have a too high back pressure at the design point. This study is an important step to develop an integrated design process with micro-compressors, the injection and suction ducts, and the CFJ airfoil to avoid the pressure mismatch.