The application relates to an aircraft aerodynamic
shape design method and
system based on a
partial differential equation, which comprises the following steps: obtaining the aerodynamic shape parameters of an aircraft and equation parameters of a
partial differential equation and inputting a large
language model constructed in advance; judging whether a closed-form analytical solution of the
partial differential equation exists according to the equation parameters, outputting an analytical formula if the closed-form analytical solution exists, analyzing an obstacle factor if the closed-form analytical solution does not exist, judging whether transformation is needed based on the obstacle factor, simplifying the partial
differential equation based on a transformation method, continuously analyzing the feasibility of operator splitting if transformation is not needed, generating a
hybrid solver code if the feasibility of operator splitting is available, performing
numerical stability analysis if the feasibility of operator splitting is not available, generating stability parameters and a pure numerical
solver code, solving the partial
differential equation based on the pure numerical
solver code and outputting flow
field data, and further optimizing the aerodynamic shape of the aircraft. Compared with the prior art, the application has the
advantage of high quality of generated solvers.