The invention discloses a parallel high-precision flutter calculation method based on a modal method, and belongs to the field of aviation aeroelasticity. Firstly, flow field mesh generation softwareperforms mesh generation on a flow field domain of an aircraft, fluent software outputs airfoil mesh node coordinates, mesh center point coordinates, surface unit global numbers and accumulated node numbers to a txt file, and structural finite element software outputs structural finite element node coordinates and modal displacement of each order. And then interpolating each order of modal displacement value to each grid node on the surface of the aircraft, reading each order of modal displacement and the txt file, calculating generalized aerodynamic force of the whole wing, solving to obtaineach order of modal generalized displacement and generalized speed, outputting the modal generalized displacement and generalized speed to the txt file, and calculating the real speed and displacementof each grid center point on the surface of the aircraft. And calculating the real displacement of the structure of each time step from the end time step. And monitoring a structural real displacement time curve of a given position, and finding out a high-precision flutter speed. According to the method, the calculation speed is increased, and the calculation cost is saved.