机翼－机身－吊架－短舱的跨声速流计算

Transonic Calculation for Wing-Body-Pylon-Nacelle Configurations

本文通过使用多块网格的嵌合体技术，计算了机翼－机身－吊架－短舱的跨声速流场。将机翼－机身－吊架－短舱流场分为机翼－机身和吊架－短舱两个子区域，根据嵌套网格结构建立机翼－机身－吊架－短舱的组合网格，分别对这两个子区域根据相应的边界条件独立求解，然后采用嵌合体技术传递两个子区域的干扰信息，通过两个流场的耦合迭代得到机翼－机身－吊架－短舱流场的计算结果，数值模拟结果与实验结果进行了比较，两者吻合较好。

A chimera grid-embedding technique is used to calculate the flowfield for complex configuration in this paper.This technique sub-divides the computational domain into simple subdomains which admit a more easilv constructed mesh.On the basis of the analysis of interaction information on the inner and outer boundaries of the overlap region,a trilinear interpolation in the isoparametric space is used in the embedding scheme for the data communication among subdomains. The solution of en-tire flowfield can be obtained through an itcrative calculation of coupling flowfields.The transonic flow for the aircraft about wing-body-pylon-nacelle configuration is calculated.The solution of numerical simulation shows agreement with experimental data.