The natural laminar flow (NLF) technology is an efficient method used to reduce wing surface turbulence friction drag significantly by delaying transition location at high Reynolds numbers. However, the existence of wide range of favorable pressure gradient on laminar flow airfoil/wing surface leads to strong shock waves occurring at the neighborhood of the trailing edge at transonic regimes. Consequently, the reduction of the friction drag is compensated with the increase of the shock wave induced drag. In this paper, a trailing edge device (TED) is applied to control shock wave on surface of designed airfoil, and the eN method based on linear stability theory (LST) is introduced to predict the flow transition location. A multi-island parallel multi-objective evolutionary algorithm (MOEA) is implemented to optimize the airfoil shape and TED configuration for obtaining a larger laminar flow region and a weaker wave drag simultaneously. Optimization results indicate that cooperative game coupled with the evolutionary algorithm optimizer can easily capture a Pareto front of this two-objective optimization problem. Numerical simulations demonstrate that both wave drag and friction drag performances of Pareto members are significantly improved compared with that of baseline. Meanwhile, the optimized airfoils equipped with TED are all have great aerodynamics performance and robustness both at design or off-design conditions.