The invention relates to the technical field of fluid dynamics, and discloses a method for calculating dynamic derivative of a flight vehicle. The method is characterized in that a static flow field boundary condition b1 I determined according to the flight state of the flight vehicle, and a solution vector, relative to the boundary condition b1, of the fluid field, is solved when a fluid field control equation is convergent to 0, namely, R=Ax+b1=0, wherein A is the matrix of the control equation; if the residual is not convergent to absolute zero, an acceptable converging residual is set as R1=Ax1+b1, and meanwhile, the aerodynamic force is as shown in the formula (seeing the description), and the equation is solved as shown in the description, wherein F is aerodynamic force; R is the residual; x is the solution vector; and thus an adjoint matrix A1 corresponding to the solution vector x1 can be obtained; a rotational angular velocity delta w is added for the flight vehicle around a reference center, and normal movement velocity is generated on the surface of the flight vehicle, and then a residual increment delta R generated by the normal velocity is calculated; the aerodynamic force increment generated by the normal velocity is as shown in the description, and as a result, the dynamic derivative of the aerodynamic force diagonal velocity can be obtained as shown in the description. According to the scheme, the method has the advantage that the solution scheme of the dynamic derivative is simple and accurate.