To avoid the singular problems in the roll axis of Nonlinear Dynamic Inversion (NDI) flight control law with common roll axis response-type, the design of a NDI flight control law with the roll axis response-type of wind-axis roll rate is discussed. Furthermore, a new slow dynamics is used inside the outer loop controller. Reference model and PI compensator are used to generate the command for outer loop controller. The control law and its performance are evaluated on a nonlinear dynamic model of an F-16 aircraft. And the new response-type is shown to yield better tacking performance by comparing with the two conventional response-types in a combined maneuver of Split-S and Cobra.