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Journal of Applied Fluid Mechanics، جلد ۱۴، شماره ۱، صفحات ۲۲۷-۲۴۱
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عنوان انگلیسی Numerical Investigation on the Response Characteristics of Hypersonic Boundary Layer under Different Types of Finite Amplitude Pulse Disturbance Waves
چکیده انگلیسی مقاله The hypersonic transient flow pass a blunt cone under three types of pulse disturbances is calculated using DNS. The response characteristic of hypersonic boundary layer among different types of pulse disturbance is compared. The distribution and evolution characteristics of disturbance modes are investigated by mode analysis. Results indicate that the receptivity characteristics induced by freestream pulse wave have both similarities and differences with that induced by freestream continuous wave. The interactions of different types of pulse waves with boundary layer and bow shock present different characteristics. The boundary layer thermodynamic characteristics under pulse fast acoustic wave are sensitive to mainstream disturbance wave, and that under pulse slow acoustic wave are sensitive to residual reflection wave. The type of pulse disturbance wave has a great influence on the production and mode distribution of boundary layer disturbance wave. In general, the disturbance amplitude in the pulse fast acoustic wave situation is the largest, the case of entropy wave is the second, and the case of slow acoustic wave is the smallest. For regional influence, the type of pulse disturbance has a huge impact on the disturbance modes in both the head and the non-head. For the three cases of pulse wave, the main mode group attenuation phenomenon which narrows the disturbance frequency band exists in the boundary layer. This group attenuation is the fastest for freestream slow acoustic wave, followed by entropy wave, and then fast acoustic wave. Under the action of pulse slow acoustic waves, the disturbance wave evolution of each order mode in the boundary layer along the streamwise is relatively stable, followed by entropy wave, and the case of fast acoustic wave is the most active.
کلیدواژه‌های انگلیسی مقاله Hypersonic flow, Disturbance type, Pulse wave, Mode analysis, Boundary Layer
نویسندگان مقاله X. Tang |
College of Engineering, Yantai Nanshan University, Yantai, Shandong, 265713, China

H. Zhang |
Beijing Spacecrafts, China Academy of Space Technology, Beijing 100094, China

H. Zhang |
Beijing Spacecrafts, China Academy of Space Technology, Beijing 100094, China

M. Shi |
College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, 150001, China

M. Shi |
College of Aerospace and Civil Engineering, Harbin Engineering University, Harbin, 150001, China

نشانی اینترنتی https://www.jafmonline.net/article_1073_01bfc08752c5c2734fa5056b6431f999.pdf
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