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Bo Yang, Hesen Yang, Ning Zhao, Hua Liang, Zhi Su and Dongsheng Zhang
The double-wedge configuration is a typical characteristic shape of the rudder surface of high-speed aircraft. The impact of the shock wave/boundary layer interaction and the shock wave/shock wave interaction resulting from the double wedge on aircraft a...
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Zhou Shen, Beimeng Hu, Guozhan Li and Hongjun Zhang
The effects of the coolant pulsation and the plasma aerodynamic actuation (PAA) on the film cooling are herein explored via large eddy simulations. The electrohydrodynamic force derived from the PAA was solved through the phenomenological plasma model. T...
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Bo Yang, Hesen Yang, Chuanbiao Zhang, Ning Zhao, Hua Liang and Dongsheng Zhang
Compression corner shock wave/boundary layer interaction (SWBLI) is a typical shock wave/boundary layer interaction (SWBLI) problem in supersonic/hypersonic flows. In previous studies, the separation flow is usually caused by a single shock wave. However...
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Zhengqi Tai, Qian Chen, Xiaofei Niu, Zhenhua Lin and Hesen Yang
In order to explore plasma-assisted turbulent mixing in aerospace engines, the dielectric barrier discharge plasma actuation for the turbulent mixing of fuel droplets and oxidant air in a ramjet combustor was studied using computational fluid dynamics. A...
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Ghazanfar Mehdi, Sara Bonuso and Maria Grazia De Giorgi
Re-ignition of aeroengines under high altitude conditions is of great importance to the safety and use of lean-burn flame. This study is focused on the experimental and numerical characterization of flow dynamics and flame re-ignition in a rectangular bu...
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Takuto Ogawa, Kengo Asada, Satoshi Sekimoto, Tomoaki Tatsukawa and Kozo Fujii
A computational study was conducted on flows over an NACA0015 airfoil with dielectric barrier discharge (DBD) plasma. The separated flows were controlled by a DBD plasma actuator installed at the 5% chord position from the leading edge, where operated AC...
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Valentina Motta, Leonie Malzacher and Dieter Peitsch
Virtual control surfaces for the optimization of steady and unsteady airloads on a compressor cascade are assessed numerically. The effects of mechanical surfaces are realized with plasma actuators, located both on the pressure and on the suction side of...
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Andreas Gross and Hermann F. Fasel
When a laminar boundary layer is subjected to an adverse pressure gradient, laminar separation bubbles can occur. At low Reynolds numbers, the bubble size can be substantial, and the aerodynamic performance can be reduced considerably. At higher Reynolds...
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