uCRM: undeflected Common Research Model
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The zip files below contain the aerodynamics and structural geometries, meshes, and other data files for two open models for high-fidelity wing aerostructural studies. uCRM-9: A flexible version of NASA’s Common Research Model configuration (https://commonresearchmodel.larc.nasa.gov/) uCRM-13.5: A higher aspect ratio version for very flexible wing design studies A full explanation of how these models were developed can be found in reference [1]. If you use the model, please cite the paper. The goal of these models is to provide a common benchmark for aerostructural analysis and design optimization of transonic flexible wing aircraft. These models were already used in various studies [2-5]. The methods used in these optimizations were originally described in reference [6]. The flight conditions are actual flight conditions and not the CRM wind tunnel conditions, so the Reynolds number differs. The conditions are: M = 0.85 CL = 0.5 Altitude = 37,000 ft uCRM-9: Re = 43,130,072 (Re length 7.01 m) uCRM-13.5: Re = 35,524,500 (Re length 5.77m) The files include: Geometry files for the wing-body-tail configuration of each aircraft (IGES/TIN) Aerodynamic mesh files for the wing-body-tail configuration of each aircraft, both in multi-block and overset format (CGNS) Structural mesh files for the aluminum wingbox structure including material properties based on a smeared stiffness blade-stiffened panel approach, external control surface and engine masses, and aerodynamic loads for the nominal cruise (BDF) Reference solutions using the MACH framework and NASTRAN All units are in SI (kg/m/s) References: 1. Brooks TR, Kenway GKW, Martins JRRA. Benchmark Aerostructural Models for the Study of Transonic Aircraft Wings. AIAA Journal. 2018 ;56(7):2840-–2855. 2. Kenway GKW, Martins JRRA. Multipoint High-fidelity Aerostructural Optimization of a Transport Aircraft Configuration. Journal of Aircraft. 2014 ;51(1):144–160. 3. Burdette DA, Martins JRRA. Design of a Transonic Wing with an Adaptive Morphing Trailing Edge via Aerostructural Optimization. Aerospace Science and Technology. 2018 ;81:192–203. 4. Burdette DA, Martins JRRA. Impact of Morphing Trailing Edge on Mission Performance for the Common Research Model. Journal of Aircraft. 2019 ;56:369–384. 5. Brooks TR, Martins JRRA, Kennedy GJ. High-fidelity Aerostructural Optimization of Tow-steered Composite Wings. Journal of Fluids and Structures. 2019 . 6. Kenway GKW, Kennedy GJ, Martins JRRA. Scalable parallel approach for high-fidelity steady-state aeroelastic analysis and adjoint derivative computations. AIAA Journal. 2014 ;52(5):935–951.
以下压缩包包含两款用于高精度机翼气动弹性研究的开源模型的气动与结构几何文件、网格文件及其他数据文件。 uCRM-9：美国国家航空航天局（National Aeronautics and Space Administration, NASA）通用研究模型（Common Research Model, CRM）构型的柔性版本（访问链接：https://commonresearchmodel.larc.nasa.gov/）； uCRM-13.5：面向超柔性机翼设计研究的大展弦比构型版本。 关于上述模型的完整开发说明可参见参考文献[1]。若您使用该模型，请引用该论文。 本系列模型旨在为跨声速柔性机翼飞行器的气动弹性分析与设计优化提供通用基准测试集。目前，上述模型已被多项研究[2-5]采用。 本系列优化所使用的方法最初见于参考文献[6]。本次采用的飞行工况为实际飞行条件，而非CRM风洞试验工况，因此雷诺数存在差异，具体工况如下：马赫数M=0.85，升力系数CL=0.5，飞行高度为37000英尺。 uCRM-9模型的雷诺数Re=43130072（特征长度7.01m）；uCRM-13.5模型的雷诺数Re=35524500（特征长度5.77m）。 本次提供的文件包括： 1. 各机型翼身尾构型的几何文件（IGES/TIN）； 2. 各机型翼身尾构型的气动网格文件，支持多块格式与重叠网格格式（CGNS）； 3. 铝制翼盒结构的结构网格文件，包含基于弥散刚度加筋板（smeared stiffness blade-stiffened panel）方法得到的材料属性、外部操纵面与发动机质量，以及名义巡航工况下的气动载荷（BDF）； 4. 基于MACH框架与NASTRAN求解得到的参考解。 所有单位均采用国际单位制（SI，单位为kg/m/s）。 参考文献： 1. Brooks TR, Kenway GKW, Martins JRRA. 跨声速机翼研究用基准气动弹性模型. AIAA Journal（《美国航空航天学会期刊》）. 2018;56(7):2840–2855. 2. Kenway GKW, Martins JRRA. 运输机构型的多点高精度气动弹性优化. Journal of Aircraft（《飞行器期刊》）. 2014;51(1):144–160. 3. Burdette DA, Martins JRRA. 基于气动弹性优化的自适应变形后缘跨声速机翼设计. Aerospace Science and Technology（《航空航天科学与技术》）. 2018;81:192–203. 4. Burdette DA, Martins JRRA. 变形后缘对通用研究模型任务性能的影响. Journal of Aircraft（《飞行器期刊》）. 2019;56(369–384). 5. Brooks TR, Martins JRRA, Kennedy GJ. 铺向可控复合材料机翼的高精度气动弹性优化. Journal of Fluids and Structures（《流体与结构期刊》）. 2019. 6. Kenway GKW, Kennedy GJ, Martins JRRA. 高精度稳态气动弹性分析与伴随导数计算的可扩展并行方法. AIAA Journal（《美国航空航天学会期刊》）. 2014;52(5):935–951.
