Abstract: Transition prediction method is crucial for simulation of flow over airfoils, since it can improve the accuracy of capturing of flow phenomena and predicting the aerodynamic forces, as well as the refined design. It is a novel data-driven transition prediction method of airfoil boundary layer by use of dynamic mode decomposition(DMD) instead of linear stabi-lity theory(LST) combining with e^N method, referred to as DMD/e^N method. Based on this method, this paper improved the DMD grid line generation method and N factor integration strategy. The improved DMD/e^N method was coupled into the RANS solver, which achieved the automation of transiton prediction for steady flows over airfoils. Transition prediction of flows around LSC72613 airfoil and NLF0416 airfoil at various angles of attack were carried out. The predicted transition locations were in reasonably good agreement with the experimental data and the results of LST/e^N method. By comparison, the calculated growth curve of N factor also accords with the envelop of LST/e^N method well, which further demonstrates the feasibility of the developed integration strategy. This will be a new powerful tool for design of NLF airfoils.