| Geometry differences between different high aircraft lift devices are large, even in the particular lift devices, takeoff, landing and cruise. Facing the complex flow, appearance, drive and support systems, it is extremely necessary to spend large of time on computing and analyzing the correction of design.The cost of wind tunnel test is high, cycle of experiment is long and the actual flight conditions cannot simulate completely. In recent years, with the improvement of computation technology, the computation flow dynamic(CFD) is applied to simulate the high aircraft lift devices widely. In this paper, based on the parameterized automatic lifting surface crack repair technology, the main works are following:(1) Summarized the current high lift configurations in lifting surface crack and the development present situation of numerical simulation technology through consulting relevant literature. Proposed the necessity of the study based on the parameters of the algorithm of the lifting surface crack repair and the improvement of the efficiency of grid generation.(2) Analyzed the advantages and disadvantages of generation time and calculation accuracy of some common methods of structural grid generation. Compared with the aerodynamic coefficients of PWT wind tunnel experiment, and verified the docking of the grid on the accuracy of numerical simulation value and the highest degree of wind tunnel experiment results.(3) Proposed a kind of automatic lifting surface crack repair based on parametric technology, includingcustom grid topology, preprocessing, the parameters of the support line structure cracks, the kernel frame line structure, mesh smoothing control, grid orthogonality control and multiple grid block adaptive reconfiguration technology, etc.(4) Exploited a set automatic repair module“GAP_FILL†based on SPIDER software platform.Verified reliabilityof the software and robustness of the algorithm through grid qualityof larges of grid examples generated and the numerical results. |
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