飞行器复杂流场高精度快速模拟分析平台及验证

The current major bottlenecks for high fidelity CFD simulation and global shape optimization of aircraft are fast high order numerical methods for solving high Reynolds number compressible N-S equations, uniform high order accuracy treatment for complex geometry and reliable boundary layer model, fast mesh generation and adaptive mesh refinement, efficient parallel computing over heterogeneous system. These are also key technologies for achievement and sustainable development of the large aircraft national major project. In this project, we intend to unify applied mathematicians, computational aerodynamicists and aerodynamic experimentalists to attack the above mentioned difficulties cooperatively. Specifically, we will construct the 3rd and higher order fast numerical methods for simulating N-S equations, propose uniform high order accuracy techniques for complex boundary treatment and physically reliable boundary layer model, develop fast Cartesian mesh generation and adaptive mesh refinement and integrate parallel software package in heterogeneous system for simulation and analysis of complex flows over aircraft. Moreover, extensive tests will be applied to verify the reliability and feasibility of the proposed methodologies, boundary layer model and the integrated software package. Finally, the software package will be applied to optimize the shape design of wing-body model for the drag reduction and flow separation control with a series of experiment supports.

高雷诺数可压缩N-S方程的高精度快速求解算法、一致高精度的复杂边界和边界层处理、快速网格生成与网格自适应加密及异构体系并行计算是目前CFD 模拟仿真完全可靠和飞行器全局优化设计的技术瓶颈，这些也是我国大飞机等国家重大专项成功实施及可持续发展的关键技术难点。本项目联合应用数学家、计算空气动力学家和空气动力学实验专家，希望通过协同研究攻克以上技术难点。具体的，本项目将发展三阶及以上精度的N-S方程快速求解算法、一致高精度边界层处理技术、笛卡尔网格快速生成及自适应加密技术，并开发异构并行系统下的飞行器复杂流场高精度快速模拟分析平台。同时，通过结合飞行器气动减阻和分离控制等关键问题，建立流动控制实验系统，以验证所发展的算法、边界层技术和数值求解平台的实用性和可靠性。

高雷诺数可压缩N-S方程的高精度快速求解算法、一致高精度的复杂边界和边界层处理、快速网格生成与网格自适应加密及异构体系并行计算是目前CFD 模拟仿真完全可靠和飞行器全局优化设计的技术瓶颈，这些也是我国大飞机等国家重大专项成功实施及可持续发展的关键技术难点。本项目联合应用数学家、计算空气动力学家和空气动力学实验专家，希望通过协同研究攻克以上技术难点。初步集成基于非结构混合网格的三维飞行器复杂流场高精度快速模拟软件平台以及基于自适应笛卡尔网格的三维复杂流场数值模拟软件平台。发展集成高阶非结构网格生成技术，发展集成非结构混合网格上针对高雷诺数NS方程的高精度高效DDG算法、DDG-DG1/FV2算法，发展基于渐进解空间的DG算法进行边界层计算，发展集成新型具有更好收敛性的WENO重构技术，发展集成自适应笛卡尔网格生成技术，发展集成笛卡尔网格交界面保精度、保守恒技术，发展集成基于笛卡尔网格的新型三阶U-MUSCL方法，发展全速域RANS方程求解算法。在两个集成的两个计算平台，针对大量的数值测试算例及应用测试算例进行了大量的平台验证测试，测试结果显示集成平台算法具有稳定性、高效性、高精度。进行了物理风洞实验，将实验结果与平台计算结果进行对比，计算结果与实验结果吻合。

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