高超声速边界层转捩研究进展与挑战

戴梧叶; 孙泓朴; 吴宁宁; 许灵芝

doi:10.13224/j.cnki.jasp.20230012

高超声速边界层转捩研究进展与挑战

doi: 10.13224/j.cnki.jasp.20230012

中国航天科工集团有限公司北京空天技术研究所，北京 100074

详细信息

作者简介:
戴梧叶（1974-），男，研究员，博士，主要从事飞行器设计、空气动力学以及CFD技术等方面的研究

通讯作者:
孙泓朴（2000-），男，硕士生，主要从事流动稳定性等方面的研究。E-mail：596424939@qq.com

中图分类号: V211.1
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- 被引次数: 0
出版历程
- 收稿日期: 2023-01-06
- 网络出版日期: 2024-06-24

Progress and challenges in hypersonic boundary layer transition

Beijing Aerospace Technology Institute，China Aerospace Science and Industry Corporation Limited，Beijing 100074，China

摘要

摘要:
对风洞试验、飞行试验、e^N方法、转捩模式以及转捩准则等常用的高超声速飞行器转捩研究方法及手段进行了介绍，并指出了这些方法在感受性原理以及转捩判据方面的改进。在此基础上，针对压缩拐角、后掠前缘、后掠翼舵面三类典型构型的高超声速转捩特性进行了详细分析，梳理出在Görtler涡增长机理以及横流不稳定性研究方面的关键问题。指出需要在加深转捩机制认知的基础上，提高静音风洞模拟能力与CFD模拟准确度来满足工程对边界层转捩预测的需求。
- 边界层转捩 /
- 高超声速 /
- 压缩拐角 /
- 后掠前缘 /
- 后掠翼舵面
Abstract:
Wind tunnel test, flight experiment, e^N method, transition mode and transition criterion were introduced, and the improvements of these methods in the sensitivity principle and transition criterion were pointed out. On this basis, hypersonic transition characteristics of compression corner, swept-back leading edge and swept-back rudder surface were analyzed in detail, and the key problems in Görtler vortex growth mechanism and cross-flow instability research were sorted out. This indicated that on the basis of deepening the understanding of transition mechanism, it is necessary to improve the simulation capability of quiet wind tunnel and the accuracy of CFD simulation to meet the needs of engineering on boundary layer transition prediction.
- boundary layer transition /
- hypersonic /
- compression corner /
- swept leading edge /
- swept wing rudder

HTML

图 1 使用热电偶测得的模型热流分布示意图^[56]

Figure 1. Model heat flow distribution measured using thermocouple^[56]

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图 2 使用TSP技术得到的模型表面温度分布^[57]

Figure 2. Surface temperature distribution of the model obtained using TSP technique^[57]

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图 3 使用NPLS技术捕捉到的流场精细结构^[58]

Figure 3. Fine structure of flow field captured using NPLS technique^[58]

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图 4 Hyper-X飞行试验^[5]

Figure 4. Flight test of Hyper-X^[5]

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图 5 HyBoLT以及凹腔和凸起^[59]

Figure 5. Concave cavity and convex of HyBoLT^[59]

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图 6 HIFiRE飞行试验模型

Figure 6. HIFiRE flight test model

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图 7 MF-1气动外形^[7]

Figure 7. Aerodynamic configuration of MF-1^[7]

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图 8 MF-1的气动现象^[7]

Figure 8. Aerodynamic phenomenon of MF-1^[7]

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图 9 超声速飞行器边界层自然转捩过程^[63]

Figure 9. Natural boundary layer transition process^[63]

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图 10 Ma=7.0，F=8.0×10⁻⁶的相速度和增长率^[67]

Figure 10. Phase velocities and growth rates of Ma=7.0，F=8.0×10⁻⁶^[67]

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图 11 三维边界层流向速度与横流速度^[16]

Figure 11. Flow velocity and cross-flow velocity in3D boundary layer^[16]

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图 12 附着线流场特征

Figure 12. Characteristics of flow field of attachment line

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图 13 Görtler失稳^[77]

Figure 13. Görtler instability^[77]

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图 14 压缩拐角处典型流动结构^[96]

Figure 14. Typical flow structure at compression corner^[96]

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图 15 航天飞机表面缺陷诱发转捩^[126]

Figure 15. Transition induced by ablation on space shuttle^[126]

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图 16 静音风洞雷诺数和马赫数的模拟能力和需求对比

Figure 16. Comparisons of Re and Mach number between low-noise wind tunnel ability and fly status

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