Conceptual study of micro-tab device in airframe noise reduction: (I) 2D computation

Kuo, Brian C.; Sarigul‐Klijn, Nesrin

doi:10.1016/j.ast.2010.02.003

Cited by 16 publications

(5 citation statements)

References 28 publications

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“…12 Comparison of flow field with different Cq Effect of different blowing rate ratios on the noise spectrum. Since this simulation is only two-dimensional, no flap side-edge related noise signal is included [12] . Slat noise is the most important source.…”

Section: Resultsmentioning

confidence: 99%

“…The technique has the acoustic pressure computed at every user-defined observer position, independently, by summing the contribution of all the sources located on a control surface [11]. The FW-H integration surface was placed such that, if expanded, no significant change in acoustic spectrum was observed [12] .The integration surface is shown in Fig. 5.…”

Section: Flow Configuration and Simulation Methodologymentioning

confidence: 99%

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Computational Investigation of the Slat Blowing Control for High-Lift Airfoil

Liu

Cui

Wang

et al. 2011

AMM

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Based on the characteristics of blowing control, a new technique was put forward to weaken slat cove separation and reduce noise. The effect of the slat blowing control on lift performance, the flow field and noise with a three-element high lift aerofoil was investigated by using the computational fluid dynamics (CFD) code of Fluent and the Reynolds-averaged Navier-Stokes equations. The blowing apertures were set on the lower surface of the slat. By using the slat blowing technique, the slat cove separation can be controlled efficiently and the lift coefficient increased. The aerodynamic performance varies with different blowing flow rates and angles of attack.

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Section: Resultsmentioning

confidence: 99%

Section: Flow Configuration and Simulation Methodologymentioning

confidence: 99%

Computational Investigation of the Slat Blowing Control for High-Lift Airfoil

Liu

Cui

Wang

et al. 2011

AMM

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show abstract

“…In study in University of California by Kuo and Sarigul-Klijn [46], numerical methods were carried to study the two dimensional unsteady flow field and acoustic components around a high-lift airfoil. Micro-tab device was designed and attached to the pressure side of the flap near its trailing-edge such that settings of high-lift devices could be reduced and hence the related airframe noise level was lowered.…”

Section: Flap Side Edge Noisementioning

confidence: 99%

Airframe Noise Sources and Reduction Technologies in Aircraft

Gorji-Bandpy

Azimi

2012

Noise & Vibration Worldwide

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The continuous increase of the air traffic linked to the operations around airports leads to increase the community noise problem. Aircraft noise is an issue of enormous environmental and technological impact. Projected growth in significant quieting of modern jet engine has brought renewed attention to the nonpropulsive component of aircraft noise. Airframe-generated noise can be the dominant component of the total noise radiated from commercial aircraft, particularly for large aircraft and especially during the landing approach. In this paper, a review of major components of airframe noise and technologies with the greatest potential to reduce airframe noise are presented.

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“…Recently, a considerable amount of experimental 5,6 and numerical [7][8][9] work has been devoted to aero-acoustics noise research regarding slats. Three main elements have been identified in the context of slat generated noise, including low to mid frequency broadband noise 10 due to the turbulent kinetic energy in the recirculation zone, tonal noise superimposed on the low-frequency broadband noise 6,10 generated by the self-excited oscillation within the slat cove, and high-frequency hump noise caused by trailing-edge vortex shedding.…”

Section: Introductionmentioning

confidence: 99%

Effect of the trailing-edge flap on tones due to self-excited oscillation within the leading-edge slat cove

Liu

Guo

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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To study the tonal noise characteristics of the leading-edge slat of high-lift configurations with and without a deployed trailing-edge flap, experiments are conducted in the D5 aero-acoustic wind tunnel at Beihang University. The numerical simulation method is used to obtain the necessary flow information. The experimental results show that low to mid frequency tonal noise generated by self-excited oscillation within the slat cove is dominant and its corresponding frequencies are basically unchanged whether the flap is deployed or not. However, the primary mode of self-excited oscillation within the slat cove switches to a higher one when the flap is deployed. Further analysis results demonstrate that variation of the primary mode is found to be closely related to the flow characteristics in the self-excited oscillation feedback loop. The number of the primary mode is generally proportional to the ratio between the vortex shedding frequency and the self-excited oscillation frequency. The flap being deployed results in an increase in the effective angle of attack of both the main wing and slat, which leads to a thinner separating boundary layer, thus increasing further the vortex shedding frequency and this ratio.

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Conceptual study of micro-tab device in airframe noise reduction: (I) 2D computation

Cited by 16 publications

References 28 publications

Computational Investigation of the Slat Blowing Control for High-Lift Airfoil

Computational Investigation of the Slat Blowing Control for High-Lift Airfoil

Airframe Noise Sources and Reduction Technologies in Aircraft

Effect of the trailing-edge flap on tones due to self-excited oscillation within the leading-edge slat cove

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