Aiming at the accuracy problem caused by the discreteness of composite materials in the dynamics modeling of the wing structure and the influence of the solution speed on the aeroelastic calculation rate of the wing, a method of establishing the dynamic model through combining the modal test and modal method is proposed. In order to improve the solution speed, the wing modal is truncated based on the modal contribution, then the static load numerical calculation and experiment verification for full modal and modal truncation were carried out. Comparing the results of the reduced modal solution and full modal solution, the error of the solution results is only about 025%, and the maximum error of the reduced modal solution is only 60% of the test result. The result shows that the experimentnumerical modeling method can accurately describe the dynamic response of the composite material wing. The modal truncation based on the modal contribution can reduce the model and greatly improve the solution speed without affecting the solution accuracy. The static and dynamic aeroelastic analyses of the wing were carried out. The analysis results show that the aeroelasticity has an unnegligible effect on the dynamic response of the wing.