面向超声速民机层流机翼设计的转捩预测方法

doi:10.7527/S1000-6893.2021.26342

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面向超声速民机层流机翼设计的转捩预测方法

聂晗^1,2, 宋文萍^1,2, 韩忠华^1,2, 陈坚强³, 段茂昌³, 万兵兵³

1. 西北工业大学航空学院环保型超音速客机研究中心/气动与多学科优化设计研究所, 西安 710072;
2. 西北工业大学翼型、叶栅空气动力学国家级重点实验室, 西安 710072;
3. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000

收稿日期:2021-09-09 修回日期:2021-09-26 出版日期:2022-11-15 发布日期:2021-12-01
通讯作者: 韩忠华,E-mail:hanzh@nwpu.edu.cn E-mail:hanzh@nwpu.edu.cn
基金资助:
国家自然科学基金（12072285，11972305）；陕西省杰出青年基金（2020JC-13）；国家数值风洞工程（2018-ZT1A03）

Automatic transition prediction for natural-laminar-flow wing design of supersonic transports

NIE Han^1,2, SONG Wenping^1,2, HAN Zhonghua^1,2, CHEN Jianqiang³, DUAN Maochang³, WAN Bingbing³

1. Research Center for Environment-Friendly Supersonic Civil Transports (ReCESST)/Institute of Aerodynamic and Multidisciplinary Design Optimization, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China;
3. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2021-09-09 Revised:2021-09-26 Online:2022-11-15 Published:2021-12-01
Supported by:
National Natural Science Foundation of China (12072285, 11972305); Shaanxi Science Fund for Distinguished Young Scholars (2020JC-13); National Numerical Windtunnel Project (2018-ZT1A03)

摘要/Abstract

摘要： 发展工程实用的转捩预测方法对于超声速民机层流减阻设计具有重要的意义。传统针对亚跨声速层流机翼设计的转捩预测方法仅考虑了二维Tollmien-Schlichting （TS）波和横流驻波诱导的转捩，无法满足超声速机翼边界层考虑三维TS斜波和横流行波的转捩预测需要。本文改进了双N因子扰动放大因子积分策略，提出了一种适用于超声速层流机翼设计的e^N方法。该方法采用固定波角和固定频率方法来寻找不稳定TS斜波和CF行波扰动，再通过固定展向波数/固定频率方法或包络线方法计算其扰动放大因子，实现了考虑TS斜波和CF行波的转捩自动判断。进一步将该方法和雷诺平均Navier-Stokes方程（RANS）求解器结合，发展了耦合e^N转捩预测的超声速机翼RANS方程数值模拟方法。针对来流马赫数2.0、后掠角65°的NASA超声速试验机翼，开展了边界层稳定性分析。结果表明，在不同雷诺数下计算得到的横流行波与驻波的扰动放大因子均与文献结果基本吻合，验证了本文方法的正确性。此外，还将本文方法应用于来流马赫数2.0、雷诺数1.39×10⁷、后掠角60°的无限翼展层流机翼初步设计。为了抑制超声速大后掠机翼边界层横流不稳定性，分析并提出了一种使流动在机翼前缘迅速加速、继而维持微弱压力梯度的理想压力分布。经数值模拟评估，设计机翼上表面接近为全层流，验证了本文方法对于超声速民机层流机翼设计的适用性。

关键词: 超声速民机, 自然层流, 线性稳定性理论, e^N方法, 转捩预测

Abstract: Automatic transition prediction is crucial for the natural-laminar-flow wing design of supersonic transports. Traditional transition prediction methods for low speed and transonic laminar-flow wing design generally only consider 2D Tollmien-Schlichting (TS) waves and stationary Crossflow (CF) waves, which are not suitable for prediction of flow transition induced by oblique TS or traveling CF waves in supersonic boundary layers. This study develops an e^N transition prediction method with an improved amplification factor computation strategy, taking into account three-dimensional oblique TS waves and traveling CF waves. This method adopts the fixed-wave-angle and fixed-frequency methods to search for unstable TS and CF modes and the fixed-transverse-wavenumber-and-fixed-frequency method or the envelope method to compute amplification factors of perturbations. The method is further coupled with a Reynolds-Averaged Navier-Stokes equation (RANS) solver for automatic transition prediction in flow simulation. The proposed method is used to analyze boundary-layer stability of NASA's experiment 65°-swept-wing at Mach number 2.0. The computed amplification factors of traveling and stationary CF waves agree well with the results in the reference work. Furthermore, the proposed method is applied to natural-laminar-flow design of an infinite-span swept wing with a swept angle of 60° at Mach number 2.0, Reynolds number 1.39×10⁷. We propose an ideal pressure distribution which quickly accelerates the flow near the leading edge and then keeps it in a mild pressure gradient. The designed wing is evaluated and nearly full laminar flow is observed over the upper surface, indicating the applicability of our method for aerodynamic design of the natural-laminar-flow wing of supersonic transports.

Key words: supersonic transports, natural laminar flow, linear stability theory, e^N method, transition prediction

中图分类号:

V211.3

聂晗, 宋文萍, 韩忠华, 陈坚强, 段茂昌, 万兵兵. 面向超声速民机层流机翼设计的转捩预测方法[J]. 航空学报, 2022, 43(11): 526342-526342.

NIE Han, SONG Wenping, HAN Zhonghua, CHEN Jianqiang, DUAN Maochang, WAN Bingbing. Automatic transition prediction for natural-laminar-flow wing design of supersonic transports[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526342-526342.

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面向超声速民机层流机翼设计的转捩预测方法

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