Aileron Buzz Simulation Using an Implicit Multiblock Aeroelastic Solver
Aileron Buzz Simulation Using an Implicit Multiblock Aeroelastic Solver
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DOI：
10.2514/2.3134
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发表时间：
2003-05
影响因子：
2.2
通讯作者：
Guowei Yang;S. Obayashi;J. Nakamichi
中科院分区：
文献类型：
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作者：
Guowei Yang;S. Obayashi;J. Nakamichi
将薄层Navier-Stokes方程与结构运动方程相耦合，发展了一种全隐式多块气动弹性解算器，用于复杂气动外形的颤振仿真。Navier-Stokes方程采用上下对称的Gauss-Seidel迭代算法和修正的Harten-Lax-van Leer-Einfeldt-Wada格式。结构运动方程在广义坐标下采用二阶直接二阶微分法进行离散。采用超限插值法对柔性曲面附近块体的网格变形进行了计算。为了评价网格变形的有效性，首先比较了具有刚性网格和变形网格的摆动LANN机翼。将该方法应用于AGARD 445.6标准气动弹性机翼颤振速度和频率的预测。最后，以日本国家航空航天实验室的超音速输运模型为例，对副翼嗡嗡声的气动弹性不稳定性进行了模拟。
A fully implicit multiblock aeroelastic solver, which coupled thin-layer Navier-Stokes equations with structural equations of motion, has been developed for the flutter simulation on complex aerodynamic configurations. Navier-Stokes equations are solved with a lower-upper symmetric Gauss-Seidel subiteration algorithm and a modified Harten-Lax-van Leer-Einfeldt-Wada scheme. Structural equations of motion are discretized by a direct second-order differential method with subiteration in generalized coordinates. The transfinite interpolation is used for the grid deformation of the blocks neighboring the flexible surface. To evaluate the effectiveness of the grid deformation, a comparison is first done for the oscillating LANN wing with a rigidly attached grid and a deforming grid. Then the method is applied to predict the flutter speed and frequency of the AGARD 445.6 standard aeroelastic wing. Finally, the aeroelastic instability referred to as aileron buzz is simulated for the supersonic transport model of the National Aerospace Laboratory of Japan.