A PNS calculation flow field-based rapid prediction method and system for transition of a high-speed boundary layer

A PNS calculation flow field-based rapid prediction method for transition of a high-speed boundary layer comprises the following steps: S1, intercepting a head grid of an aircraft, and obtaining an NS equation laminar flow field of the head of the aircraft by adopting a numerical simulation method; s2, extracting flow field information of the outlet cross section of the head grid of the aircraft, wherein the flow field information comprises point coordinates of the outlet cross section of the head grid of the aircraft, three speed components of corresponding flow field speed in a rectangular coordinate system, and temperature and pressure of the outlet cross section; s3, taking an aircraft head outlet section flow field as an inlet condition of PNS continuous calculation, and carrying out PNS space propulsion calculation; and S4, performing transition indication on a PNS laminar flow field at the downstream of the head of the aircraft by adopting an eN method based on a linear stability theory. According to t