| 结冰模拟软件AERO-ICE中的关键数值方法 |
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| 引用本文： | 李浩然,段玉宇,张宇飞,陈海昕. 结冰模拟软件AERO-ICE中的关键数值方法[J]. 航空学报, 2021, 42(z1): 726371-726371. DOI: 10.7527/S1000-6893.2021.26371 |
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| 作者姓名： | 李浩然 段玉宇 张宇飞 陈海昕 |
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| 作者单位： | 清华大学 航天航空学院, 北京 100084 |
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| 基金项目： | 国家自然科学基金（11872230，91852108）；航空科学基金（2020Z006058002）；国家重大项目（GJXM92579） |
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| 摘 要： | 自然积冰对于航空飞行安全造成重大隐患，飞机在穿越富含过冷水汽的云层时冰形将按一定的物理规律积聚生长。介绍了一款三维结冰数值模拟软件AERO-ICE，该软件由网格自动生成、空气流场RANS计算、水滴场欧拉方法计算、结冰热力学分析四个模块组成。在空气流场计算方面，采用SPF k-v2-ω湍流模型，该模型引入湍流非平衡特性修正，预测的带冰翼型最大升力系数和失速攻角相对SA和SST模型有显著的提高。水滴场欧拉方程由于源项较大，迭代求解时容易发散，AERO-ICE软件采用流场光顺、二阶MUSCL空间离散以及LU-SGS隐式时间推进方法改善了数值稳定性。在结冰热力学分析模块，AERO-ICE软件同时具有Messinger与Myers模型，并将Messinger模型预估的壁面温度作为Myers模型的边界条件，从而解决了Myers模型温度设置的经验性问题。AERO-ICE软件支持多块网格、多重网格加速技术与大规模并行计算，其冰形计算结果得到了初步的验证。
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| 关 键 词： | 飞机结冰 结冰热力学分析 欧拉方法多相流 水膜流动 非流线体大分离 |
| 收稿时间： | 2021-09-01 |
| 修稿时间： | 2021-09-14 |
Numerical method of ice-accretion software AERO-ICE |
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| LI Haoran,DUAN Yuyu,ZHANG Yufei,CHEN Haixin. Numerical method of ice-accretion software AERO-ICE[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(z1): 726371-726371. DOI: 10.7527/S1000-6893.2021.26371 |
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| Authors: | LI Haoran DUAN Yuyu ZHANG Yufei CHEN Haixin |
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| Affiliation: | School of Aerospace Engineering, Tsinghua University, Beijing 100084, China |
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| Abstract: | Natural ice-accretion poses threat to aviation flight safety. When an aircraft passes through the clouds containing supercooled water droplet, ice could be accumulated according to certain physical laws. This paper introduces a three-dimensional icing simulation software AERO-ICE. The software is composed of four modules: automatic grid generation, RANS calculation of air flow field, Euler calculation of water drop field and thermodynamic analysis of icing. In the calculation of the air flow field, the SPF k-v2-ω turbulence model is adopted, which introduces the fixing term of non-equilibrium characteristics of turbulence. The model is developed to improve the prediction of non-streamlined large separation flow. Because of the large source term, the solving process of the Euler equation of the water field can be hard to converge. AERO-ICE software uses flow field smoothing, second-order MUSCL space discretization and LU-SGS implicit time marching method to improve numerical stability. In the icing thermodynamic analysis module, the AERO-ICE software has both Messinger and Myers models. The wall temperature predicted by the Messinger model is used as the boundary condition of the Myers model. This method solves the empirical problem of temperature setting in the Myers model. AERO-ICE software supports multi-block gird, multi-grid acceleration technology and large-scale parallel computing. The calculation of the ice-accretion has been preliminarily verified. |
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| Keywords: | aircraft icing icing thermodynamic analysis Euler method multiphase flow calculation water film flow non-streamlined body with large separation |
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