Titlebook: Advances in Effective Flow Separation Control for Aircraft Drag Reduction; Modeling, Simulation Ning Qin,Jacques Periaux,Gabriel Bugeda Boo

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Textbooks in Mathematical Sciencesayers and the Reynolds stresses. 3D simulations using improved delayed detached eddy simulation, a hybrid RANS/LES technique, has been used for the study. The geometry for the study is taken from the experimental configurations for this case. The case comprises a turbulent flow over a backward facin

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Chaos in Differential Equations,g step geometry. 2D and 3D simulations were carried out indicating that optimisation of plasma operating parameters is only reliable when dealing with 3D simulations. It was found that there is a parameter space in which reduction in reattachment length takes maximum values, up to 22% reduction, and

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Textbooks in Mathematical Sciences 1 million. We analyzed the impact of the transient attachment and separation process on the mean and turbulent fields. To control the flow, angled fluidic vortex generators through 44 orifices were positioned in a single array at a position of 30% from the leading edge of the airfoil. PIV measureme

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Periodic Orbits and Limit Sets,nergy input. In this paper numerical investigation on flow control with moving surface over a NACA0015 airfoil is conducted with a Reynolds Averaged Navier-stokes (RANS) based approach, in which the moving surface is implemented with mounting two rotating cylinders at leading edge and leeward side o

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Textbooks in Mathematical Sciencesement techniques to the actuator types which turned out to be most promising in the previous investigations. The selected devices were synthetic jet actuators from NUAA and plasma actuators from CNRS. Both actuator types were investigated in a backward facing step (BFS) geometry. Additional measurem

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https://doi.org/10.1007/978-3-030-32538-1ol methods are conducted in a low speed wind tunnel. Results show that the maximum lift coefficient of the taking-off/landing configuration can be increased by 40.8%, and the stall angle of attack can be increased by 4.34° with jets flow control devices on wing; while the maximum lift coefficient ca

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https://doi.org/10.1007/978-3-030-32538-1ic jet is generated from a 2 mm horizontal slot which is at up corner of the step and facing downstream direction. In order to investigate the effectiveness of the synthetic jet at different actuation frequencies (0, 35, 50 and 100 Hz), 2C-2C particle image velocimetry and fluorescence oil-film was