The research on the structure of T800 carbon fiber composite has just started in our country, so it is necessary to make a systematic study on the stability of stiffened panel with T800 carbon fiber reinforced composite. The test articles of 8 configurations are designed by varying the skin thickness, stiffener spacing, stiffener geometric parameters, and the compression stability tests are carried out. Considering the influence of the lateral boundary condition and the effective width of skin, two commonly used compression buckling load engineering calculation methods are verified. Results show that when the moment of inertia increases the buckling load will increase in the same stiffener area, the failure load of stiffened panels mainly depends on the cross sectional area of the panels, and the effect of skin thickness and stiffener spacing on buckling load is greater than that on failure load; For the thin skin, when the lateral simply supported and the effective width of skin is b=D-b2/2, the calculated value is closest to the experimental value; For the thick skin, when the lateral simply supported and the effective width of skin is b=D, the calculated value is closest to the experimental value.