uCRM: undeflected Common Research Model

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翼面气动-结构耦合研究的开源模型的气动与结构几何文件、网格及其他数据文件。两款模型分别为：uCRM-9：NASA通用研究模型(Common Research Model, CRM)的柔性版本（访问地址：https://commonresearchmodel.larc.nasa.gov/）；uCRM-13.5：适用于超柔性翼面设计研究的高展弦比版本。 关于这些模型的完整开发说明可参见参考文献[1]。若使用本数据集的模型，请引用该论文。 本数据集的核心目标是为跨音速柔性翼面飞行器的气动-结构耦合分析与设计优化提供通用基准测试模型。上述模型已被多项研究[2-5]采用。 本次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工况，而非CRM风洞试验工况，因此雷诺数(Reynolds number, Re)存在差异，具体工况参数如下：马赫数(Mach number, M)=0.85，升力系数(Lift coefficient, CL)=0.5，飞行高度为37000英尺。 两款模型对应的雷诺数分别为：uCRM-9：Re=43130072（特征长度7.01m）；uCRM-13.5：Re=35524500（特征长度5.77m）。 本次提供的文件包含以下内容： ① 两款飞行器的翼身尾构型几何文件，格式为初始图形交换规范(IGES)/三角不规则网络(TIN)； ② 两款飞行器的翼身尾构型气动网格文件，同时支持多块网格与重叠网格格式，格式为CFD通用符号系统(CGNS)； ③ 铝合金翼盒结构的结构网格文件，包含基于弥散刚度片条加筋板(smeared stiffness blade-stiffened panel)方法的材料属性、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，格式为BDF(Bulk Data Format)； ④ 基于MACH框架(MACH framework)与NASTRAN求解器(NASTRAN)得到的参考解。 所有单位均采用国际单位制（kg/m/s）。 参考文献： 1. Brooks TR, Kenway GKW, Martins JRRA. 跨音速翼面研究用基准气动-结构模型. 《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-结构优化. 《飞行器学报》, 2014;51(1):144–160. 3. Burdette DA, Martins JRRA. 基于气动-结构优化的自适应变弯度后缘跨音速翼面设计. 《航空航天科学与技术》, 2018;81:192–203. 4. Burdette DA, Martins JRRA. 自适应变弯度后缘对通用研究模型任务性能的影响. 《飞行器学报》, 2019;56(3):369–384. 5. Brooks TR, Martins JRRA, Kennedy GJ. 铺向可控复合材料翼面的高精度气动-结构优化. 《流体与结构学报》, 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. 《美国航空航天学会期刊》, 2014;52(5):935–951.