The invention discloses a rotating missile rotating speed characteristic aerodynamic optimization method. The method comprises the following steps: S1, determining parameters of a genetic algorithm; S2, determining aerodynamic configuration feature sizes influencing the rolling driving torque and the damping torque, and arranging the aerodynamic configuration feature sizes to serve as a chromosomecombination of a genetic algorithm; S3, determining the feature size as a gene segment, and setting a reasonable feasible range of the feature size; S4, determining a fitness function; S5, randomly determining an initial parent population; S6, performing chromosome gene crossing and mutation operation on the parent population to form a filial generation population; S7, performing CFD calculationon each individual in the parent population and the filial population to obtain six-component aerodynamic force, and substituting the six-component aerodynamic force into the dynamics simulation model; S8, substituting the key overall indexes of the simulation model into the fitness function, and screening out a new population with the best performance to serve as a parent of the next generation;and S9, repeating the steps S6-S8 until an evolution ending condition is met. According to the method, the problem of discontinuous strong coupling global optimization of aerodynamic configuration optimization of the rotating speed characteristics of the rotating missile can be solved.