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An efficient method for flutter prediction by solving the Euler and boundary-layer equations on non-moving Cartesian grids.

机译：通过求解非移动笛卡尔网格上的Euler和边界层方程，可以有效地进行颤振预测。

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This dissertation presents an efficient inviscid-viscous coupling method for airplane wing flutter prediction. For the inviscid part, the Euler method is employed for accurate resolution of shock-waves and vorticity. For viscous effects, an integral boundary-layer method is developed and coupled with the Euler solver in a semi-inverse manner. In order to avoid the burden of generating body-fitted grids as well as the difficulty of transferring displacements and forces between the structural and aerodynamic grids involved in flutter simulations, non-moving Cartesian grids are used by the Euler solver. The thickness of the wing as well as its small-scale motion is accounted for by approximate boundary conditions which are implemented on the stationary wing-chord plane.; The proposed method of Cartesian Euler coupled with an integral boundary-layer is first validated by steady flow and forced pitching flow simulations, and then used for wing flutter-boundary predictions. The resulting solver is much more efficient than a Reynolds-Averaged-Navier-Stokes (RANS) solver while yielding results of comparable accuracy. In addition, the proposed method eliminates large amounts of human labor for problem setup due to the use of Cartesian grids.
机译：本文提出了一种有效的飞机机翼颤振预测的粘粘耦合方法。对于不粘部分，采用欧拉方法来精确解析冲击波和涡度。对于粘性效应，开发了积分边界层方法，并以半反方式与Euler求解器耦合。为了避免产生适合人体的网格的负担以及避免在颤动模拟中涉及的结构网格和空气动力学网格之间传递位移和力的困难，欧拉求解器使用了不移动的笛卡尔网格。机翼的厚度及其小尺度运动是由近似的边界条件决定的，该条件在固定的翼弦平面上执行。首先通过稳定流和强迫俯仰流模拟验证了所提出的与整体边界层耦合的笛卡尔欧拉方法，然后将其用于机翼颤振边界预测。生成的求解器比雷诺平均Navier-Stokes（RANS）求解器效率高得多，同时产生的结果具有可比的精度。另外，由于使用笛卡尔网格，所提出的方法消除了用于问题设置的大量人力。

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