The invention relates to a numerical
simulation method for obtaining aircraft flow fields, wherein an interrupted
Galerkin method based on non-structural right angle meshes is used to solve the flow field, and right angle meshes with a
quadtree structure are used to disperse a to-be-solved flow field area into a set of meshes; each
quadrilateral mesh is processed by dual-linear coordinate conversion, so each mesh under a current physical coordinate
system can be mapped onto the next regular mesh in a computational coordinate
system, so standard square meshes can be obtained; conservation variables in units under the computational coordinate
system are obtained through numerical computation; a front face, a
lower face, a left face and a right face of each mesh under the physical coordinate system are determined; according to differences between the left and right vibrations of unit interfaces, an interrupted
detector is established; and the conservation variables in each mesh are processed by flow field display on the disperse meshes, so flow field distribution can be obtained. According to the invention, the interrupted
Galerkin method based on the non-structural right angle meshes is introduced into flow field computation, so accuracy of the flow field computation is increased, and complicated flow phenomena can be solved.