As the main bearing structure of civil aircraft, the fuselage frame is of great significance to the weight of the aircraft. A hoop bending test was carried out on the composite fuselage curved panels with C- and Z-type integral frames to study the failure mode and load-bearing capacity of the integral frame, as well as the influence of lateral support on the load-bearing capacity of the frame. A pair of force couple was used to apply bending load on the panel. The modified engineering algorithms and FE models were used to predict the failure load and compare with the test results. The research shown that C-type integral fame should be selected as the main design plan because of the better design redundancy. The arrangement of lateral support was the key to improve the load capability of the integral frame, as it could affect the failure mode. The modified engineering algorithms could predict the frame lateral stability, effectively, which could be used for calculation iterations of the integral frame size and lateral support ar-rangement, rapidly. However, the engineering algorithm for inner flange local stability was not conservation, and the FE method should be used for optimization iteration.