典型文献
Experimental investigation of expansion effect on shock wave boundary layer interaction near a compression ramp
文献摘要:
The experiment is conducted to investigate the effect of expansion on the shock wave boundary layer interaction near a compression ramp.The small-angle expansion with an angle degree of 5° occurs at different positions in front of the compression ramp.The particle image velocimetry and flow visualization technology show the flow structures,velocity field,and velocity fluctuation near the compression ramp.The mean pressure distribution,pressure fluctuation,and power spectral density are measured by high-frequency response pressure transducers.The experi-mental results indicate that the expansion before the compression ramp position affects the shock wave boundary layer interaction to induce a large-scale separation.But the velocity fluctuation and pressure fluctuation are attenuated near the large-scale flow separation region.When the expansion occurs closer to the compression ramp,the expansion has a more significant impact on the flow.The fluctuation of velocity and pressure is significantly attenuated,and the wall pressure rise of the sep-aration point is reduced obviously.And the characteristic low-frequency spectrum signal related to the unsteadiness of the shock wave boundary layer interaction is significantly suppressed.In addi-tion,variation of the separation region scale at different compression angle degrees is distinctive with the effect of expansion.
文献关键词:
中图分类号:
作者姓名:
Junjie HUO;Shihe YI;Wenpeng ZHENG;Haibo NIU;Xiaoge LU;Dundian GANG
作者机构:
College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China
文献出处:
引用格式:
[1]Junjie HUO;Shihe YI;Wenpeng ZHENG;Haibo NIU;Xiaoge LU;Dundian GANG-.Experimental investigation of expansion effect on shock wave boundary layer interaction near a compression ramp)[J].中国航空学报(英文版),2022(12):89-101
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B类:
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AB值:
0.423659
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