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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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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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Bao Liu, Maarten Vanierschot and Frank Buysschaert
The present work examines the capabilities of two transition models implemented in ANSYS Fluent in the open-water performance prediction of a rim-driven thruster (RDT). The adopted models are the three-equation ??-????-??
k
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k
L
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and the four-equati...
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Dapeng Wei, Bilong Liu and Ludi Kang
The control of decentralized velocity feedback on curved aircraft plates under turbulent boundary layer excitations is numerically investigated in this paper. Sixteen active control units are set on the plate to reduce the vibration and sound radiation o...
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Pavel Polivanov, Oleg Vishnyakov and Andrey Sidorenko
The problem of flow control under conditions of a turbulent boundary layer at transonic and supersonic free-stream velocities is considered. Such flows are integral components of the flight process and exert significant effects on the flow around both th...
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John-Paul Mosele, Andreas Gross and John Slater
Shock wave boundary layer interactions are common to both supersonic and hypersonic inlet flows. Wall-resolved implicit large-eddy simulations of a canonical Mach 2.5 axisymmetric shock wave boundary layer interaction experiment at Glenn Research Center ...
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Alexander Kotvitskii, Pavel Kazanskii and Ivan Moralev
The pulse electric arc discharge in an external magnetic field is studied as a vortex generator in the subsonic boundary layer. A pulsed Ampere force induces a hairpin vortex near the wall; its structure depends on the relative direction of arc propagati...
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Sergey Chernyshev, Gadzhi Gadzhimagomedov, Aleksandr Kuryachiy, Dmitry Sboev and Stepan Tolkachev
In a subsonic wind tunnel, a three-dimensional separation of a developed turbulent boundary layer was simulated on a swept wing flap model. A multi-discharge plasma actuator operating on the basis of dielectric barrier discharge was used to overcome the ...
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Tingkai Dai and Bo Zhang
Shock wave/turbulent boundary layer interaction (SBLI) is one of the most common physical phenomena in transonic wing and supersonic aircraft. In this study, the compression ramp SBLI (CR-SBLI) was simulated at a 24° corner at Mach 2.84 using the open-so...
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Giannino Ponchio Camillo, Alexander Wagner, Takahiko Toki and Carlo Scalo
This work investigates a hypersonic turbulent boundary layer over a 7°" role="presentation">7°7°
7
°
half angle cone at a wall-to-total temperature ratio of 0.1, M∞=7.4" role="presentation">??8=7.4M8=7.4
M
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=
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