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Wing aeroelasticity analysis based on an integral boundary-layer method coupled with Euler solver
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作者 Ma Yanfeng He Erming +1 位作者 zeng xianang Li Junjie 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2016年第5期1262-1272,共11页
An interactive boundary-layer method, which solves the unsteady flow, is developed for aeroelastic computation in the time domain. The coupled method combines the Euler solver with the integral boundary-layer solver ... An interactive boundary-layer method, which solves the unsteady flow, is developed for aeroelastic computation in the time domain. The coupled method combines the Euler solver with the integral boundary-layer solver (Euler/BL) in a "semi-inverse" manner to compute flows with the inviscid and viscous interaction. Unsteady boundary conditions on moving surfaces are taken into account by utilizing the approximate small-perturbation method without moving the computational grids. The steady and unsteady flow calculations for the LANN wing are presented. The wing tip displacement of high Reynolds number aero-structural dynamics (HIRENASD) Project is simulated under different angles of attack. The flutter-boundary predictions for the AGARD 445.6 wing are provided. The results of the interactive boundary-layer method are compared with those of the Euler method and experimental data. The study shows that viscous effects are significant for these cases and the further data analysis confirms the validity and practicability of the coupled method. 展开更多
关键词 Aeroelasticity FLUTTER Integral boundary-layer Transonic flow Unsteady flow
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