Gaining air superiority in guided missiles through multi-objective optimization derived from genetic algorithm is one of the latest techniques to increase the range of a guided missile in the military industry. This article is a research about the optimization of the aerodynamic variables of a projectile to achieve the maximum range and the maximum weight of the cargo (warhead) by considering the main surfaces of the wing and the control surfaces of the bulk. For this purpose, the disciplines of stability and controllability, Weight and balance aerodynamics and trajectory were chosen as the main issues in the conceptual design phase of the guided projectile. The guided projectile design problem has four design variables and two objective functions, including payload weight and range. Semi-empirical software has been used to calculate the aerodynamic coefficients and the link of its outputs to the three-degree-of-freedom flight simulator code in MATLAB software and the genetic algorithm code. In the continuation of the article, by analyzing the codes, it can be seen about 15.84% for the projectile range and about 3.37% for the warhead weight.