采用自适应直角网格计算三维增升装置绕流

针对三维增升装置绕流，对存在剪刀叉的不连续外形，基于自适应直角网格，提出并介绍了分区和面搭接技术，采用变长宽比网格，进行了直角网格生成和流场Euler方程数值计算. 根据几何外形的特点，在直角网格生成过程中，以外形不连续面作为分区边界，对初始``根'网格实施分区处理，降低了整个网格的生成难度. 通过基于外形的自适应网格加密，详细描述了剪刀叉外形和缝道，提高了网格质量. 在分区边界面上，基于面搭接技术，构造重叠面积切割算法，实现边界两侧网格间的流场信息传递，保证流场计算中的通量守恒. 采用中心有限体积方法，结合双时间推进算法，完成了两段机翼、带增升襟翼翼身组合体绕流流场的Euler方程数值模拟，对计算结果与实验数据进行了对比，验证了所提方法、算法的合理性和实用性.

Numerical analysis of flows around 3-D high-lift system by adaptive cartesian grid method

Because of the complexities in both configuration and flow field,there are great difficulties inthe numerical simulation of flow around 3-D high-lift system.In this paper,computations of complex flowfield around 3-D high-lift configurations using an adaptive Cartesian grid method and cell-center finite volumeapproach are carried out and compared to wind-tunnel experiments.The main emphasis is laid on a multi-zonetechnique and face-to-face algorithm and its applications.A modified Cartesian grid method is introducedto simulate the complex flow by using the adaptive grid technique.A multi-zone technique and face-to-facealgorithm are presented and employed to simplify the great difficulties in grid generation,and to establish theflow field information exchange on the multi-zone interface.We solve Euler equations using cell-centred finitevolume method and dual-time stepping scheme.The above algorithms and techniques have been validated onsome test cases involving a two-partial-span flap wing and a wing-fuselage model with flap.The computedresults show that the grid generation and the flow calculation are feasible,and show that the present methodsare effective one for solving flow field over the complex 3-D high-lift systems.