A Method for Predicting the Symmetric Cross-watershed Flow Field of an Aircraft Plane

Abstract

The invention discloses a method for predicting a symmetrical cross-watershed flow field of an aircraft, which relates to the field of cross-watershed flow field simulation, including: solving the flow field based on the first physical space grid corresponding to the aircraft and the incoming flow conditions to obtain the flow field Velocity and temperature information; generate a three-dimensional velocity space grid, set the grid range of the three-dimensional velocity space grid based on the outer boundary to obtain a three-dimensional hemispherical area, obtain a hemispherical encrypted area and a spherical encrypted area, based on the grid spacing distribution information, A hemispherical velocity space grid is generated from the hemispherical encrypted area and the spherical encrypted area, and the spherical velocity space grid is obtained by symmetrically copying the hemispherical velocity space grid; based on the first physical space grid and the spherical three-dimensional velocity space grid The iterative solution is carried out to obtain the three-dimensional physical space flow field of the aircraft; the invention realizes the rapid prediction of the symmetrical cross-watershed flow field of the aircraft.

Description

technical field [0001] The invention relates to the field of cross-watershed flow field simulation, in particular to a method for predicting a plane-symmetric cross-watershed flow field of an aircraft. Background technique [0002] With the development of near space vehicles, cross-basin flow fields where continuous flow and rarefied flow coexist are becoming more and more common. At present, it is generally solved by NS / DSMC partition overlap or Boltzmann equation, but the selection of continuous failure parameters and the interface of the former The judging process is more complicated, and the latter has developed rapidly in recent years due to the use of the same control equation in multiple watersheds. Xu et al. proposed the Unified Gas Kinetic Scheme (UGKS), which couples the particle collision and migration process, and realizes the automatic transition of the equation between continuous flow and rarefied flow by adjusting the relaxation time. It has been widely used ...

AI Technical Summary

Problems solved by technology

However, in the UGKS algorithm, the unstructured velocity space grid generated by conventional methods often cannot guarantee the plane symmetry of the grid, which makes the distribution function processing in the symmetric boundary very complicated, and interpolation processing is required in most cases, which affects the calculation precision

In order to avoid complex symmetric boundary processing and ensure calculation accuracy, many researchers directly perform cross-basin flow field simulations on full-scale aircraft even for surface-symmetric flow field simulations with symmetrical shapes, resulting in a waste of computing resources.

Images