The invention belongs to flight control technologies, and provides a civil aircraft air flow angle estimation method based on a pneumatic model. The method comprises the step 1 of calculating out a total lift coefficient CL and a total side force coefficient CY of an aircraft; the step 2 of utilizing an aerodynamic force wind tunnel experiment to obtain an interpolation table of aerodynamic coefficients generated by all components; the step 3 of classifying aerodynamic force generated by all the components; the step 4 of obtaining a variable polynomial of degree N of an attack angle, and obtaining a variable polynomial of degree M of a sideslip angle; the step 5 of overlaying a plurality of parameters of the variable polynomial of degree N of the attack angle to obtain a total variable polynomial of degree N of the attack angle, and overlaying a plurality of parameters of the variable polynomial of degree M of the sideslip angle to obtain a total variable polynomial of degree M of the sideslip angle; the step 6 of reversely solving the attack angle through the variable polynomial of degree N, and reversely solving the sideslip angle through the variable polynomial of degree M; the step 7 of determining a real-time attack angle and a real-time sideslip angle according to actual value ranges of the attack angle and the side slip angle.