A technique for generating structured meshes for wings with finite-span flaps is presented. The method consists of four steps. They are: selecting fronts, determining the degree-of-guidedness, determining front-advancement priority, and then advancing the front. A hyperbolic predictor and elliptic corrector are used to advance the fronts. The final block grid is both CO and C1 continuous. Fronts are automatically created where needed and merged where not needed. Front connectivity defines a parameter called degree-of-guidedness, or D. O. G., which determines the topology of the grid that will be generated. Individual fronts are advanced in an order specified by their surface topology. The method is used to generate structured meshes around wings with partial span split and hinged flaps. The examples shown are model flaps on a North American P-51 Mustang wing. The mesh generation steps are shown as well as the final mesh. The meshes generated are for illustrative purposes, and are not intended to be used in a flow solver.
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机译：提出了一种用有限跨翼片产生用于翼的结构丝网的技术。该方法由四个步骤组成。它们是：选择前部，确定引导程度，确定前进优先级，然后推进前部。使用双曲线预测器和椭圆校正器来推导前部。最终块网格均为CO和C1连续。前端将自动创建，并在不需要的地方合并。前连接定义称为引导程度的参数，或D. O. G.，它决定将生成的网格的拓扑。各个前端以其表面拓扑指定的顺序高级。该方法用于在具有部分跨度分割和铰接翼片周围产生周围的结构化网格。所示的例子是北美P-51野马翼上的模型襟翼。显示网格生成步骤以及最终网格。产生的网格用于说明性目的，并且不旨在用于流动求解器。
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