Numerical Analysis of a Trailing Edge with Triangular Serrations Using Dynamic Mode Decomposition

Thomareis, Nikitas; Papadakis, George

doi:10.2514/6.2016-2084

54th AIAA Aerospace Sciences Meeting 2016

DOI: 10.2514/6.2016-2084

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Numerical Analysis of a Trailing Edge with Triangular Serrations Using Dynamic Mode Decomposition

Nikitas Thomareis

George Papadakis

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Cited by 3 publications

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“…Thomareis et al [20] employed a dynamic mode decomposition to illustrate that the serrated trailing edge of a NACA 0012 airfoil can significantly reduce both the time-averaged and fluctuating components of the drag compared to the blunt trailing edge airfoil, due to attenuation of the turbulence energy by decorrelating the spanwise coherence of the vortices.…”

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confidence: 99%

Control of cylinder wake flow and noise through a downstream porous treatment

Mao

2019

Aerospace Science and Technology

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Various passive and active methods have been developed to control flow separation from bluff bodies. However, these methods require adjusting features of the solid surface, such as modifying its geometry or porosity, or applying external force or momentum. This paper develops an off-body-based method, without adjusting any features of the solid surface, for controlling the unsteady flow separation by fixing porous materials downstream of bluff bodies. Numerical study on flow past a circular cylinder at a subcritical Reynolds number is performed, and the result indicates that the added downstream porous material changes flow in the wake and re-laminarizes the turbulent flow around the curved cylinder surface, reducing the wall pressure fluctuation around the cylinder. therefore, the associated aerodynamic noise is reduced greatly.

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mentioning

confidence: 99%

Control of cylinder wake flow and noise through a downstream porous treatment

Mao

2019

Aerospace Science and Technology

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Dynamic mode decomposition analysis of flow separation control on wind turbine airfoil using leading−edge rod

Zhong

Liu

2023

Energy

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A Parametric Investigation of Wake Loss Reduction by using Serrated Trailing Edge in a High-speed Compressor Cascade

Liu

Fei-peng

et al. 2017

International Journal of Turbo &Amp; Jet-Engines

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The influence of the serration with different widths, angles and spanwise locations on the wake of a high-speed compressor cascade is parametrically investigated by numerical simulation. The effect mechanisms of the serration on the cascade performance are discussed in detail and the potential at the off-design points is also validated. The results show that the momentum inputted by the serration jet and the fluid exchange induced by the dominant jet vortex could reenergize the low energy corner region and weaken the trailing edge shedding vortex. With the upstream shift of the serration valley, the loss reduction and pressure rise are enhanced due to the strengthened jet and counter-rotating vortex pair, whereas the flow turning is reduced by the decreased camber angle and the enhanced jet deflection. The serration at the blade height corresponding to the core of the low energy fluid could perform better for the loss reduction, whereas the serration close to the endwall could obtain higher pressure rise. For the optimal serration located at 12.5 % blade height with a width of 5 mm and an angle of 45 °, the loss is reduced by 8.9 % and the pressure rise is increased by 2.2 %, with the flow turning slightly reduced by 0.93 °

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Numerical Analysis of a Trailing Edge with Triangular Serrations Using Dynamic Mode Decomposition

Cited by 3 publications

References 23 publications

Control of cylinder wake flow and noise through a downstream porous treatment

Control of cylinder wake flow and noise through a downstream porous treatment

Dynamic mode decomposition analysis of flow separation control on wind turbine airfoil using leading−edge rod

A Parametric Investigation of Wake Loss Reduction by using Serrated Trailing Edge in a High-speed Compressor Cascade

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