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Yanxin Yin, Ruiyang Lu, Jianxin Liu and Zhangfeng Huang
Temperatures within the boundary layers of high-enthalpy hypersonic flows can soar to thousands or even tens of thousands of degrees, leading to significant real gas phenomena. Although there has been significant research on real gas effects on hypersoni...
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Yunfeng Wu, Qingkuo Li, Hang Yuan, Ziliang Li, Shiji Zhou, Ge Han and Xingen Lu
High-pressure ratio centrifugal compressors? diffusers face challenges from high-velocity, non-uniform flow at the impeller outlet, decreasing efficiency and stall margin. To address this, this paper presents a novel vaned diffuser passage design method ...
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Ranran Huang, Tao Xue and Jie Wu
A two-point cylindrical-focused laser differential interferometer (2P-CFLDI) system and a conventional Z-type Schlieren were used to measure the hypersonic turbulent boundary layer on a flat plate at Mach number Ma = 6 and Reynolds number Re = 1.08 × 106...
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Kyohei Hanazaki and Wataru Yamazaki
Busemann?s supersonic biplane airfoil can reduce wave drag through shock interactions at its designed freestream Mach number. However, a choking phenomenon occurs with a decrease in the freestream Mach number, and the drag coefficient increases significa...
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Xin Wei, Xiaojuan Shi, Honghu Ji and Jinlong Hu
In order to study the infrared radiation characteristics of an air-breathing hypersonic vehicle powered by a scramjet, it is necessary to solve the internal and external flow field of the air-breathing hypersonic vehicle. Owing to the complexity and diff...
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Yi-Xuan Huang and Kung-Ming Chung
The flow field in a cavity depends on the properties of the upstream boundary layer and the cavity geometry. Comprehensive studies for rectangular cavities have been conducted. This experimental study determines the global surface pressure pattern for el...
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Alexander Hergt, Tobias Danninger, Joachim Klinner, Sebastian Grund, Manfred Beversdorff and Christian Werner-Spatz
In this paper, an experimental and numerical investigation of the effect of leading-edge erosion in transonic blades was performed. The measurements were carried out on a linear blade cascade in the Transonic Cascade Wind Tunnel of DLR in Cologne at two ...
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Fangyou Yu, Zhanbiao Gao, Qifan Zhang, Lianjie Yue and Hao Chen
Suppressing shock-induced flow separation has been a long-standing problem in the design of supersonic vehicles. To reduce the structural and design complexity of control devices, a passive control technique based on micro-serrations is proposed and its ...
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Lakshmi Narayana Phaneendra Peri, Antonella Ingenito and Paolo Teofilatto
The goal of this paper is to investigate the aerodynamic and aerothermodynamic behavior of the Schiaparelli capsule after the deployment of a supersonic disk-gap-band (DGB) parachute during its re-entry phase into the Martian atmosphere. The novelty of t...
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Luping Zhao, Yawen Shao and Wei Jia
Mach number, as an important index to judge the system performance in wind tunnel tests, its stability determines the quality of the flow field of this wind tunnel and needs to be controlled precisely. Due to the complex process in the wind tunnel test, ...
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