Abstract
Transverse pressure gradient (TPG) is one of the key factors influencing the boundary layer airflow diversion in a bump inlet. This paper proposes a novel TPG-based hypersonic bump inlet design method. This method consists of two steps. First, a parametric optimization approach is employed to design a series of 2D inlets with various compression efficiencies. Then, according to the prescribed TPG, the optimized inlets are placed in different osculating planes to generate a 3D bump inlet. This method provides a means to directly control the aerodynamic parameters of the bump rather than the geometric parameters. By performing this method to a hypersonic chin inlet, a long and wide bump surface is formed in the compression wall, which leads to good integration of the bump/inlet. Results show that a part of the near-wall boundary layer flow is diverted by the bump, resulting in a slight decrease in the mass flow but a significant improvement in the total pressure recovery. In addition, the starting ability is significantly improved by adding the bump surface. Analysis reveals that the bump has a 3D rebuilding effect on the large-scale separation bubble of the unstarted inlet. Finally, a mass flow correction is performed on the designed bump inlet to increase the mass flow to full airflow capture. The results show that the mass flow rate of the corrected bump inlet reaches up to 0.9993, demonstrating that the correction method is effective.
概要
目的
在超/高超声速进气道中, 横向压力梯度是鼓包对边界层气流产生排移的关键, 然而目前基于横向压力梯度的鼓包设计方法还有待进一步发展. 本文旨在提出一种横向压力梯度驱动的高超声速鼓包进气道设计方法, 以实现鼓包型面上横向压力梯度完全可控. 在此基础上分析鼓包对进气道性能的影响, 并从流动层面解释其原因.
创新点
1. 提出了一种由横向压力梯度驱动的高超声速鼓包进气道设计方法, 实现了鼓包与进气道完全一体化的设计;2. 明晰了鼓包型面对不起动进气道大尺度分离区的三维重构作用, 进而解释了鼓包进气道起动性能改善的原因.
方法
1. 通过对鼓包工作原理的分析, 提出一种基于横向压力梯度的高超声速鼓包进气道设计方法;2. 通过数值仿真, 研究鼓包进气道在设计点下对边界层气流的排移效果(图14);3. 通过数值仿真和风洞实验相结合的方法, 研究鼓包对不起动进气道大尺度分离区的三维重构作用, 进而分析鼓包对进气道起动过程的作用机理.
结论
1. 采用本文提出的方法实现了由横向压力梯度驱动的鼓包型面设计, 且该型面与进气道外压缩面完全一体化;2. 在横向压力梯度的作用下, 一部分边界层气流被排移出进气道, 使得进气道流量系数稍有下降, 但总压恢复性能明显提高;3. 鼓包型面对不起动状态下的进气道大尺度分离区具有三维重构作用, 使得进气道起动性能得到提高;4. 采用本文提出的流量修正方法可使鼓包进气道实现全流量捕获.
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Acknowledgments
This work is supported by the National Natural Science Foundation of China (No. 12102470) and the Hunan Provincial Innovation Foundation for Postgraduate (No. CX20200082), China.
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Shang-cheng XU, Yi WANG, and Zhen-guo WANG designed the research. Shang-cheng XU and Bing XIONG processed the corresponding data. Shang-cheng XU wrote the first draft of the manuscript. Bing XIONG helped to organize the manuscript. Yi WANG and Xiao-qiang FAN revised and edited the final version.
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Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiaoqiang FAN, and Bing XIONG declare that they have no conflict of interest.
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Xu, Sc., Wang, Y., Wang, Zg. et al. Design method for hypersonic bump inlet based on transverse pressure gradient. J. Zhejiang Univ. Sci. A 23, 479–494 (2022). https://doi.org/10.1631/jzus.A2100532
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DOI: https://doi.org/10.1631/jzus.A2100532
Key words
- Hypersonic bump inlet
- Transverse pressure gradient (TPG)
- Boundary layer flow
- Total pressure recovery
- Starting ability
- Mass flow correction