基于工程转捩模型的高超声速进气道特性

杨慧; 路文睿; 李虹杨; 岳连捷

doi:10.13700/j.bh.1001-5965.2017.0516

基于工程转捩模型的高超声速进气道特性

doi: 10.13700/j.bh.1001-5965.2017.0516

杨慧^{1, 2, ,},
路文睿^{1, 2},
李虹杨³,
岳连捷⁴

1.
北京航空航天大学能源与动力工程学院, 北京 100083
2.
先进航空发动机协同创新中心, 北京 10008
3.
航空工业沈阳飞机设计研究所, 沈阳 110035
4.
中国科学院力学研究所, 北京 100080

详细信息

作者简介:
杨慧  女, 博士, 讲师。主要研究方向：叶轮机械气动弹性数值模拟和实验

路文睿  女, 硕士研究生。主要研究方向：叶轮机械流动数值模拟、叶片颤振数值模拟

李虹杨  男, 博士研究生。主要研究方向：高超声速流动数值模拟, 流/热耦合数值模拟

通讯作者:
杨慧.E-mail:huiyang@buaa.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: 2017-07-31
- 录用日期: 2017-08-11
- 网络出版日期: 2018-07-20

Hypersonic air inlet performance based on engineering transition model

YANG Hui^{1, 2
, ,},
LU Wenrui^{1, 2},
LI Hongyang³,
YUE Lianjie⁴

1.
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Collaborative Innovation Center for Advanced Aero-Engine, Beijing 10008
3.
AVIC Shenyang Aircraft Design Research Instiute, Shenyang 110035, China
4.
Institute of Mechanics, Chinese Academy of Sciences, Beijing 100080, China

More Information

Corresponding author: YANG Hui.E-mail:huiyang@buaa.edu.cn

摘要

摘要:
为研究高超声速进气道的性能参数随飞行高度、来流湍流度及来流马赫数的变化规律，并考察其压缩面上的边界层转捩现象对进气道性能的影响，采用本课题组程序平台HGFS所发展的γ-Re_θ转捩模型进行了一系列的数值模拟工作，并对相应的流动现象和机理进行分析。首先，利用进气道压缩面的简化模型对γ-Re_θ转捩模型经验关联公式的高超声速改进方法进行了验证；其次，以某型等熵压缩面的高超声速进气道为对象，研究了飞行高度、来流马赫数对边界层转捩位置等多个参数的影响。结果表明：随着飞行高度的增加，压缩面上边界层转捩位置延后，进气道总压恢复系数下降；与地表情况相比，在设计飞行高度转捩位置延后了约0.525 m，边界层厚度增加了约73%，总压恢复系数下降了约3.2%；来流湍流度变化0.5%量级可导致转捩位置移动0.2 m左右，但来流湍流度对总压恢复系数的影响则很小。
- 高超声速进气道 /
- 转捩模型 /
- 飞行高度 /
- 湍流度 /
- 数值模拟
Abstract:
In order to study the variation of the performance parameters of a hypersonic air inlet with the flight height, free stream turbulence intensity and free stream Mach number, and the influence of the boundary layer transition on the compression surface on air inlet performance, a series of numerical simulations were conducted by using the γ-Re_θ transition model developed in a in-house HGFS and the flow phenomena and mechanisms were analyzed. Firstly, the improved γ-Re_θ transition model implemented in the HGFS code was verified using a simplified model of an air inlet compression surface. Secondly, a hypersonic air inlet with isentropic compression surface was studied the effect of flight height and Mach number on parameters such as the transition location. Main conclusions are as follows:with the increase of the flight height, transition location of the boundary layer moves downstream on the compression surface, and the total pressure recovery coefficient decreases. Compared with the ground surface state, at the design flight height, the transition location moves downstream for about 0.525 m, the boundary layer thickness increases by about 73%, and the total pressure recovery coefficient decreases by 3.2%. About 0.5% magnitude change of the inflow turbulence intensity will contribute to 0.2 m movement of the transition location. However, the influence of turbulence intensity on the total pressure recovery coefficient is quite small.
- hypersonic air inlet /
- transition model /
- flight height /
- turbulence intensity /
- numerical simulation

HTML全文

图 3 前缘带倒圆的压缩面的计算网格

Figure 3. Computational mesh for blunt leading edge compression surface

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图 1 Re_θt与Tu的新的经验关联曲线

Figure 1. New empirical correlation curves of Re_θt vs Tu

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图 2 高超声速飞行器进气道示意图

Figure 2. Schematic of air inlet of hypersonic aircraft

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图 4 不同模型计算的静压和流线分布

Figure 4. Distribution of static pressure and streamline calculated by different models

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图 5 计算得到的压力系数和斯坦顿数与实验值的对比

Figure 5. Comparison of calculated pressure coefficient and Stanton number with expemental values

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图 6 高超声速进气道的计算域和网格

Figure 6. Computational domain and mesh of hypersonic air inlet

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图 7 计算得到的设计状态静压分布

Figure 7. Distribution of computed static pressure under design condition

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图 8 压力系数和壁面摩阻系数随飞行高度的变化

Figure 8. Variation of pressure coefficient and skin friction resistance coefficient with flight height

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图 9 分离泡强度随飞行高度的变化(Ma_∞=6.0)

Figure 9. Variation of separation bubble strength with flight height (Ma_∞=6.0)

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图 10 速度型曲线随飞行高度的变化(x=1.85 m)

Figure 10. Variation of velocity profile with flight height (x=1.85 m)

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图 11 压力系数和壁面摩阻系数随来流湍流度的变化

Figure 11. Variation of pressure coefficient and skin friction resistance coefficient with free stream turbulence intensity

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图 12 静压和流线随来流马赫数的变化

Figure 12. Variation of static pressure and streamline with free stream Mach number

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图 13 壁面摩阻系数随来流马赫数的变化

Figure 13. Variation of skin friction resistance coefficient with free stream Mach number

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表 1 部分性能参数随飞行高度的变化

Table 1. Variation of some performance parameters with flight height

飞行高度/km	总压恢复系数	边界层厚度(相对值)/%	转捩位置/m
0	0.750	8.8	0.025
5	0.750	9.6	0.04
10	0.749	10.4	0.065
15	0.743	11.2	0.12
20	0.733	12.0	0.24
23	0.725	13.6	0.35
26	0.718	15.2	0.55

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表 2 部分性能参数随来流湍流度的变化

Table 2. Variation of some performance parameters with free stream turbulence intensity

来流湍流度/%	总压恢复系数	转捩位置/m
0.5	0.705	0.7
1.0	0.703	0.55
1.5	0.700	0.35
1.75	0.699	0.25
2.5	0.697	0.1

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表 3 部分性能参数随来流马赫数的变化

Table 3. Variation of some performance parameters with free stream Mach number

来流马赫数	总压恢复系数	转捩位置/m
4.2	0.721	0.18
4.5	0.729	0.26
5.0	0.741	0.34
5.5	0.746	0.64
6.0	0.704	0.64
6.5	0.617	0.64
7.0	0.523	0.64

下载: 导出CSV

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