Abstract:

　A ch imera grid2embedding technique is used to calculate the flow field fo r w ing2body2pylon2nacelle configurat ion. Th is technique subdivides the computat ional domain into simp lesubdomains w h ich adm it a mo re easily const ructed meshes. O n the basis of the analysis of inter2act ion info rmat ion on the inner and the outer boundaries of the overlap region, a t rilinear interpo lat ion in the isoparamet ric space is used in the embedding scheme fo r the data communicat ionamong subdomains. The so lut ion of the ent ire flow field can be obtained th rough an iterat ive calculat ion of coup ling flow fields. The t ransonic flow fo r w ingbodypylon2nacelle configurat ion ofC25A aircraft is calculated. The so lut ion of numerical simulat ion show s agreement w ith experimental data.

Key words: chimera grid embedding scheme, wingbody ?store, pylonnacelle, pylonmissile