Abstract
Abstract A structured overset-grids method with enhanced implicit hole-cutting has been developed to simulate the flow around aircraft configurations, especially high-lift configurations. The current research uses the implicit hole-cutting method to improve the automation of domain connectivity and optimize the overlapping areas. Some enhancements for the original implicit hole-cutting method are proposed to make it more effective. Furthermore, a simple method for calculating the force on the overlapping solid surfaces is also presented. Jameson's second-order finite volume method is utilized to solve the Navier-Stokes equations. A wing-body configuration and two high-lift configurations are numerically tested and the numerical results are compared with the experimental data.
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