With regard to the fuselage stiffened panel, it is essential to attain the stress intensity factor, and the core work is to calculate the geometrical factor. According to the analysis method of the stiffened panel structure which was put forward by Swift, the corresponding analysis tool was programmed,by which the geometrical factor of the fuselage panel with circumferential was obtained, then the theoretical result was compared with other result which was computed by finite element analysis. In the last, the geometrical factor was input into the Nasgro software which was adopted to carry out the crack growth analysis, the life was almost identical with the test result. This method was pretty efficiency, it can help save a lot of time and money and have a strong engineering application value.