Langtry-Menter转捩模型的高超声速修正与验证

李城锐; 江中正; 吴昌聚; 杨雨欣; 邓思超

doi:10.13224/j.cnki.jasp.20220970

Langtry-Menter转捩模型的高超声速修正与验证

doi: 10.13224/j.cnki.jasp.20220970

1.
浙江大学航空航天学院，杭州 310027
2.
中国运载火箭技术研究院研究发展部，北京 100076

基金项目: 国家自然科学基金 (U20B2007)

详细信息

作者简介:
李城锐（1995−），男，博士生，主要从事流动转捩和气动优化设计研究

通讯作者:
江中正（1991−），男，讲师，博士，主要从事稀薄气体动力学研究。E-mail：jzhongzh@zju.edu.cn

中图分类号: V211.3
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- 被引次数: 0
出版历程
- 收稿日期: 2022-12-22
- 网络出版日期: 2024-02-29

Hypersonic modification and verification of Langtry-Menter transition model

1.
School of Aeronautics and Astronautics，Zhejiang University，Hangzhou 310027，China
2.
Research and Development Department，China Academy of Launch Vehicle Technology，Beijing 100076，China

摘要

摘要:
针对高超声速边界层转捩流动预测问题，基于传统Langtry-Menter转捩模型和SST（shear stress transport）湍流模型开展高速修正方法研究，将高超声速横流判据修正、湍动能压力膨胀项可压缩性修正和压力梯度系数修正引入到原始转捩模型，以拓展模型在高超声速边界层流动转捩的预测能力，并采用超声速平板、0°攻角高超声速直锥、小攻角高超声速尖锥和HIFiRE-5等6个典型算例对修正后的转捩模型的预测能力进行验证。研究结果表明：修正后的转捩模型所预测的转捩起始位置、转捩终点位置和转捩区长度与实验结果基本吻合，壁面摩擦阻力和热流的计算结果与实验测量结果基本一致，修正后的转捩模型对高超声速边界层转捩的预测能力较好。
- 高超声速流动 /
- 边界层 /
- 横流判据 /
- 流动转捩 /
- 湍流模型
Abstract:
For the prediction of hypersonic boundary layer transition flow, three types of high-speed modified methods were studied based on the traditional Langtry-Menter transition model and SST （shear stress transport） turbulence model. The modification of hypersonic cross-flow criterion, compressibility modification of turbulent kinetic energy pressure dilatation term and modification of pressure gradient coefficient were introduced into the original transition model to expand the simulation capacity of the model in hypersonic flow. The modified transition model was validated by using several typical cases: supersonic plate, hypersonic cone with zero angle of attack, hypersonic cone with small angle of attack and hypersonic HIFiRE-5. The results showed that the predicted transition-start position, transition-end position and transition zone length of the modified model were basically consistent with the experimental results. The calculated results of skin friction and heat flux were basically consistent with the experimental measurement data. The modified transition model performed well in predicting hypersonic transition flow.
- hypersonic flow /
- boundary layers /
- cross-flow criterion /
- transition flow /
- turbulence models

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图 1 不同网格的摩擦阻力系数分布曲线对比

Figure 1. Comparison of skin friction coefficient distribution curves for different grids

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图 2 超声速绝热壁平板摩擦阻力系数分布

Figure 2. Skin friction coefficient distribution for adiabatic hypersonic flate plate

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图 3 不同网格的壁面压力分布对比

Figure 3. Comparison of wall pressure distribution for different grids

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图 4 不同网格的壁面斯坦顿数对比

Figure 4. Comparison of wall Stanton number for different grids

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图 5 算例1壁面热流密度分布

Figure 5. Heat flux distribution on wall for case 1

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图 6 算例2壁面热流密度分布

Figure 6. Heat flux distribution on wall for case 2

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图 7 迎风面中心线斯坦顿数分布和实验温升值

Figure 7. Stanton number distribution and experimental temperature rise for windward centerline

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图 8 背风面中心线斯坦顿数分布和实验温升值

Figure 8. Stanton number distribution and experimental temperature rise for leeward centerline

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图 9 计算网格和边界条件示意图

Figure 9. Schematic of computational grid and boundary conditions

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图 10 壁面流线和无量纲压力p/p_∞云图

Figure 10. Streamline patterns and contours of p/p_∞

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图 11 壁面流线和马赫数云图

Figure 11. Streamline patterns and contours of Mach number

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图 12 HIFiRE-5中心线上的涡

Figure 12. Vortex on the centerline of HIFiRE-5

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图 13 数值模拟结果与实验结果对比

Figure 13. Comparison between computational and experimental results

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表 1 4套计算网格的属性

Table 1. Properties of the four sets of grids

网格	网格数量（流向×法向）	第一层网格间距/ μm
Grid A	175×120	10
Grid B	219×190	5
Grid C	259×200	1
Grid D	329×220	0.5

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表 2 高超声速圆锥计算条件

Table 2. Calculation conditions for the hypersonic cone

算例	$ M{a_\infty } $	$ {T_\infty }/{\mathrm{K}} $	$ {\rho _\infty }/ （{\mathrm{kg}}/{{\mathrm{m}}^3}） $	$ R{e_\infty }/10^6\;{\mathrm{m}}^{-1} $	$ {T_{{\mathrm{wall}}}}/{\mathrm{K}} $
1	7.15	231.1	0.07060	9.92	301.0
2	6.58	214.0	0.12568	16.7	301.3
注：表中下标$\infty $表示来流参数，T_wall表示壁面温度。

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表 3 3套直锥计算网格的属性

Table 3. Properties of three sets of straight cone grids

网格	网格数量（流向×法向×周向）	第一层网格间距/ μm
Grid 1	104×60×13	10
Grid 2	186×101×31	1
Grid 3	226×150×37	0.5

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