Effects of the aerothermoelastic deformation on the performance of the three-dimensional hypersonic inlet
Effects of the aerothermoelastic deformation on the performance of the three-dimensional hypersonic inlet
复制标题
气动热弹性变形对三维高超声速进气道性能的影响
DOI：
10.1016/j.ast.2018.11.015
复制
发表时间：
2019-01
影响因子：
5.6
通讯作者：
Wu Jie
中科院分区：
文献类型：
--
作者：
Ye Kun;Ye Zhengyin;Li Chunna;Wu Jie
高超声速进气道在同时承受气动载荷和恶劣气动载荷时，更容易发生变形。此外，高超声速进气道的流场对结构非常敏感。因此，有必要研究气动热弹性变形对高超声速进气道流动结构和性能的影响。本研究基于CFD/CSD耦合方法建立了松散耦合静态气动热弹分析框架，分析中采用单向和双向气动热弹耦合。此外，还详细研究了气动热弹性变形对三维高超声速进气道流动结构和性能的影响。通过DLR高超声速进气道实验模型和HIRENASD实验模型验证了CFD方法和CFD/CSD耦合方法的可靠性。两种耦合方法得到的结果是相似的。然而，通过双向耦合方法获得的气动热弹性变形相对较大，变形对进气道性能的影响更为明显。气动热弹性变形的最大值存在于进气道前缘。这种变形改变了唇部附近的激波结构，增强了进气道内的激波强度，增加了分离区长度和外壁温度，改变了出口的流场。气热弹性变形会导致质量流量系数和压升比的增大；但会降低总压恢复系数。
The hypersonic inlet is more prone to deform when simultaneously subjected to aerodynamic load and harsh aerothermodynamic load. Moreover, the flow field of the hypersonic inlet is sensitive to configuration. Therefore, it is necessary to investigate the effects of the aerothermoelastic deformation on the flow structure and the performance of the hypersonic inlet. This study develops a loose coupling static aerothermoelastic analysis framework based on the CFD/CSD coupling method, and the one-way and the two-way aerothermal-aeroelastic coupling are both used in the analysis. Furthermore, the effects of the aerothermoelastic deformation on the flow structure and the performance of a three-dimensional hypersonic inlet are studied in detail. The reliabilities of the CFD method and the CFD/CSD coupling method are verified by the validation cases of DLR hypersonic inlet experimental model and the HIRENASD experimental model. The results obtained by the coupling methods are similar. However, the aerothermoelastic deformation obtained through the two-way coupling method is relatively larger, and the effects of the deformation on the inlet performance are more obvious. The maximum of the aerothermoelastic deformation exists at the leading edge of the inlet lip. The deformation changes the shock wave structure near the lip, strengthens the shock wave intensity inside the inlet, increases the length of the separated region and the temperature of the external wall, and changes the flow field of the exit. The aerothermoelastic deformation will lead to the increasing of the mass flow coefficient and the pressure rise ratio; however, it will decrease the total pressure recovery coefficient.
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DOI：
10.2514/6.2009-7397
发表时间：
2009-10
期刊：
--
影响因子：
--
作者：
J. McNamara;A. Culler;Andrew R. Crowell
通讯作者：
J. McNamara;A. Culler;Andrew R. Crowell
DOI：
10.2514/4.862540
发表时间：
1996-09
期刊：
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影响因子：
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DOI：
10.2514/3.10301
发表时间：
1989-11
期刊：
--
影响因子：
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作者：
A. Wieting;M. Holden
通讯作者：
A. Wieting;M. Holden
影响因子：
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作者：
A. Culler;J. McNamara
通讯作者：
A. Culler;J. McNamara
DOI：
10.2514/6.2001-2881
发表时间：
2001-06
期刊：
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影响因子：
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作者：
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A. Kuranov;V. Kuchinsky;E. Sheikin