Investigation of Airframe Noise from High Lift Configuration Model

Ura, Hiroki; Yokokawa, Yuzuru; Imamura, Taro; Ito, Takeshi; Yamamoto, Kazuomi

doi:10.2514/6.2008-19

Cited by 24 publications

(42 citation statements)

References 12 publications

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“…If the SCF profile is larger than the slat shear layer profile then the flow at the slat gap gets restricted, which consequently affects the velocity peak and aerodynamic performances of the main-element. Nevertheless, a SCF profile that eliminates the large vortices in the slat cove region at the same time maintaining the aerodynamic performance is highly favourable as they are viable source of noise reduction, as shown by Imamura et al [13,14], Tao [18] and also in the current experimental study (see Sec. III.C).…”

Section: Pressure Coefficient Distributionmentioning

confidence: 70%

“…As part of the noise reduction study of the MDA airfoil, a slat cove filler (SCF) has been designed using similar strategy introduced by Imamura et al [13,14] for experimentation purposes. Initially, preliminary RANS steady state simulations for the Baseline case were performed at the angle of attack 8…”

Section: Slat Cove Filler Designmentioning

confidence: 99%

“…Imamura et al and Ura et al from JAXA showed experimentally and computationally [13,14] that even though noise reduction can be achieved by the use of SCF, its profile significantly affects the aerodynamic lift characteristics of the three-element airfoil. They tested two SCF profiles that were designed based on the flow field streamlines of angles of attack 0…”

mentioning

confidence: 99%

“…Eventhough several studies [9][10][11][12][13][14][15][16][17][18] have been performed on the noise reduction capabilities of the slat cove filler, only basic aerodynamic and noise measurements have been presented. A detailed experimental study of the aerodynamic performance characteristics such as surface pressure measurements, shear layer measurements and the interaction confluent wakes of all the three-element of the high-lift airfoil has not yet been reported.…”

mentioning

confidence: 99%

“…Several experimental and computational studies [9][10][11][12][13][14][15][16][17][18] were made over the past decade to reduce the broadband noise arising from the slat cove region by filling the recirculation area within the slat cove gap. Even though reduction in broadband noise was observed at all the instances it has been a challenge to maintain the aerodynamic performance of the high-lift device for the cove filled configurations.…”

mentioning

confidence: 99%

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Experimental Investigation of Flow Around Three-Element High-Lift Airfoil with Morphing Fillers

Jawahar

Azarpeyvand

Silva

2017

23rd AIAA/CEAS Aeroacoustics Conference

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms Campos, 12227-901, Brazil Aerodynamic and aeroacoustic measurements of a three-element airfoil (30P30N) fitted with various slat cove fillers and droop-slat configuration were carried out for a wide range of angles of attack and Reynolds numbers (4.6 × 10 5 to 1.1 × 10 6 ). The results are presented for static and unsteady surface pressure measurements and flow visualisation using particle image velocimetry. Mean surface pressure measurement results show that the aerodynamic performances were affected with the application of slat cove filler especially if its profile was not apt for the operating conditions. The PIV results clearly show that a highly energised fixed vorticity was present within the slat cove region of the baseline case and it was eliminated by the application of slat cove filler. A smaller vorticity develops as a result of the slat cove filler and the vortices size changes with increase in angle of attack. The wall-pressure spectra acquired using the flush mounted transducers shows narrowband and broadband components for the baseline case. The application of slat cove fillers completely eliminated the narrowband spectra generated by the vortices inside the slat cove. However, the slat cove filler appears to increase the overall broadband at low and mid-frequency range in the airfoil near-field. Results confirmed the great aerodynamic and aeroacoustic potential of the morphing structures for high-lift devices, which is one of the highly sought candidate for the next generation aircraft control surfaces.

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Section: Pressure Coefficient Distributionmentioning

confidence: 70%

Section: Slat Cove Filler Designmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Experimental Investigation of Flow Around Three-Element High-Lift Airfoil with Morphing Fillers

Jawahar

Azarpeyvand

Silva

2017

23rd AIAA/CEAS Aeroacoustics Conference

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Flow characteristics of slat cove fillers

Jawahar

Theunissen

Azarpeyvand

et al. 2020

Aerospace Science and Technology

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Experimental measurements using Particle Image Velocimetry were carried out to understand the flow characteristics of a 30P30N high-lift airfoil with and without slat cove fillers. The tests were carried out for the 30P30N airfoil with a retracted chord of c = 0.35, at angles of attack of α = 6 • and 12 • , and for a chord-based Reynolds number of Re c = 7.0 × 10 5 . The wall pressure fluctuation results show that the use of slat cove fillers eliminates the slat tonal noise component. The results of the mean flow fields such as the normalized mean velocity, Reynolds stress components, and turbulent kinetic energy are presented for the baseline, half-slat cove filler, and slat cove filler configurations. The velocity contour results with streamlines showed a recirculation region within the slat cavity. The use of the half-slat cove filler reduced the size of the recirculation region and the use of the slat cove filler eliminated the recirculation region. The mean velocity and turbulent kinetic energy profiles at the slat wake showed no difference between the three tested configurations. The Particle Image Velocimetry results were further analyzed using Proper Orthogonal Decomposition. The results showed that the first two eigenmodes of the vorticity with the highest energy were contained within the slat shear layer and vortex shedding emanating from the slat cusp for the baseline case. The energy levels were distributed over the slat shear layer for the half-slat cove filler and slat cove filler configurations as the vortex shedding is suppressed by the use of the slat cove fillers.

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RETRACTED: Flap side edge noise modeling and prediction

Guo

2013

Journal of Sound and Vibration

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Investigation of Airframe Noise from High Lift Configuration Model

Cited by 24 publications

References 12 publications

Experimental Investigation of Flow Around Three-Element High-Lift Airfoil with Morphing Fillers

Experimental Investigation of Flow Around Three-Element High-Lift Airfoil with Morphing Fillers

Flow characteristics of slat cove fillers

RETRACTED: Flap side edge noise modeling and prediction

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