Numerical aerodynamic and aeroelastic investigations are conducted for the Common Research Model (CRM) configuration with deployable aileron control surfaces and a trimmable horizontal stabilizer at cruise and off-cruise conditions. The numerical methodology which is implemented in the multi-disciplinary simulation environment SimServer is based on CFD and coupled CFD-CSM simulations. The DLR Tau Code is applied in order to solve the Reynolds-Averaged-Navier-Stokes (RANS) equations. The Spalart-Allmaras turbulence model with Edwards modification is used for the closure modeling of the three-dimensional RANS equations. A linear modal solver is utilized to calculate structural displacements and rotations of control surfaces are modeled by a Chimera approach. A grid independence study is conducted by using the rigid aerodynamic model of the CRM. The main focus of the analysis lies on the evaluation of the stationary CFD-CSM simulations addressing the influence of structural deformation on aileron effectiveness. Influences of various flow conditions and different fuel tank filling levels on the resulting local and global aerodynamic properties of the CRM are investigated. The reduction of aileron effectiveness as well as the difference in horizontal trim deflection angle if structural elastic effects are considered is investigated for the considered Mach number range and aircraft mass configurations.

中文翻译：

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结构弹性对偏转控制面常用研究模型气动特性的影响


对通用研究模型 (CRM) 配置进行了数值空气动力学和气动弹性研究，该配置具有可展开的副翼控制面和巡航和非巡航条件下的可调整水平稳定器。在多学科仿真环境 SimServer 中实施的数值方法基于 CFD 和耦合 CFD-CSM 仿真。应用 DLR Tau 代码来求解雷诺平均纳维斯托克斯 (RANS) 方程。采用 Edwards 修正的 Spalart-Allmaras 湍流模型用于三维 RANS 方程的闭合建模。利用线性模态求解器来计算结构位移，并通过 Chimera 方法对控制面的旋转进行建模。使用 CRM 的刚性空气动力学模型进行网格独立性研究。分析的主要重点在于评估静态 CFD-CSM 模拟，解决结构变形对副翼有效性的影响。研究了各种流动条件和不同油箱填充水平对 CRM 局部和整体空气动力学特性的影响。对于所考虑的马赫数范围和飞机质量配置，研究了副翼效率的降低以及考虑结构弹性效应时水平配平偏转角的差异。