Fore-loaded airfoil has less pitching moment and better stealth ability, it can have both good aerodynamic and stealth per-formances at the same time. It is ideal airfoil for flying wing aircraft. Multi-points integrated optimization design research of Fore-loaded airfoil is present in this paper based on a flying wing aircraft. Airfoil parametric method, aerodynamic performance evaluation method and optimization algorithm are applied during the research. Firstly, geometry control abil-ities of classical airfoil parametric methods are evaluated, and the evaluation results shows that Hicks-Henne and CST methods have more powerful control abilities. Then, the design states and optimization model are established according to the flying wing aircraft design requirements. The integrated optimization design of Fore-loaded airfoil is implemented afterwards with CST parametric method, NS equation numerical solution method and genetic algorithm, and satisfying design result is obtained. Compared with the reference airfoil, the optimized airfoil has larger relative thickness and better aerodynamic performance.