Aircraft profile rapid inverse design method based on high-performance numerical calculation

The invention discloses an aircraft profile rapid inverse design method based on high-performance numerical calculation, which comprises the following steps: S1, after the profile of an inverse design object is determined, performing digital model reverse reconstruction based on collected parameter information; s2, performing CFD flow field calculation based on the reconstructed digital model; s3, confirming the aerodynamic configuration of the digital model based on the flow field resolving result of S2; and S4, performing function inverse design and digital model evaluation verification on the confirmed digital model. The invention discloses an aircraft profile rapid inverse design method based on high-performance numerical calculation, a high-performance numerical calculation solver based on a graphics processing unit (GPU) is introduced in CFD flow field solution, compared with the prior art, the aircraft flow field solution time can be greatly shortened by adopting the high-performance numerical calculat