严格考虑副翼端面和机翼切口流动而运用嵌套网格方法，生成了带副翼三维机翼的计算网格 。 流场计算采用雷诺平均Navier-Stokes方程和Johnson-King湍流模型。数值计算结果与实 验值吻合很好。%Failing to find details about chimera grid calculation in the open lecture, we researched and developed such details ourselves. In section 2 we discussed Johnson-King turbulence model in much detail and derivedeqs. (1) through (9 ) . This discussion and the nine equations formed the core of our research and dev elopment. With the chimera embedding technique, we divided the entire flowfield into small sub-regions with overlapping grids. In each sub-region, we, aided by eqs. (1) through (9) derived for the Johnson-King turbulence model, solved the Re ynolds-averaged Navier-Stokes equations by iteration; after each iteration, our algorithm provided automatic boundary information exchanges among different sub -regions. We used a certain delta wing as numerical example. Simulation results as shown in Fig.3, 4 and 5 show good agreement with experimental data.
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