Aerodynamic Noise Reduction for High-Lift Devices on a Swept Wing Model

Streett, Craig L.; Casper, Jay; Lockard, David P.; Khorrami, Mehdi R.; Stoker, Robert W.; Elkoby, Ronen; Wenneman, Wayne F.; Underbrink, James R.

doi:10.2514/6.2006-212

Cited by 64 publications

(63 citation statements)

References 22 publications

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“…However no aerodynamic measurements were presented in this study. Streertt et al further investigated noise and basic aerodynamics of the SCF setup using trapezoidal wing swept model fitted [10]. The results showed noise reduction to be sensitive to the angle of attack and SCF modification.…”

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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.…”

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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.…”

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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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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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“…These links abate the aerodynamic noise generated by airflow around the discontinuous flap side edge by extending and continuously fairing a flexible moldline into the wing trailing edge. A flow analysis 35 illustrating the mechanism and the effect on flap side-edge streamlines is shown in Fig. 7.…”

Section: Methods Of Analysismentioning

confidence: 99%

An Analytical Assessment of NASA's N+1 Subsonic Fixed Wing Project Noise Goal

Berton

Envia

Burley

2009

15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference)

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The Subsonic Fixed Wing Project of NASA's Fundamental Aeronautics Program has adopted a noise reduction goal for new, subsonic, single-aisle, civil aircraft expected to replace current 737 and A320 airplanes. These so-called "N+1" aircraft -designated in NASA vernacular as such since they will follow the current, in-service, "N" airplanes -are hoped to achieve certification noise goal levels of 32 cumulative EPNdB under current Stage 4 noise regulations. A notional, N+1, single-aisle, twinjet transport with ultrahigh bypass ratio turbofan engines is analyzed in this study using NASA software and methods. Several advanced noise-reduction technologies are empirically applied to the propulsion system and airframe. Certification noise levels are predicted and compared with the NASA goal.

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“…The National Aeronautics and Space Administration (NASA) Acoustic Research Measurements (ARM) project was established by the NASA Flight Demonstrations and Capabilities (FDC) project to evaluate the noise reduction benefits of the Adaptive Compliant Trailing Edge (ACTE) technology along with various main landing gear (MLG) noise reduction concepts. The ACTE replaced the Fowler flaps on the NASA SubsoniC Research Aircraft Testbed (SCRAT) and created a seamless trailing edge, which previous studies had shown to have the potential to yield significant noise reduction benefits [2]. The ACTE noise reduction efforts are grouped under the Seamless Trailing Edge ACTE Acoustics Measurements (STEAAM) effort.…”

Section: Introductionmentioning

confidence: 99%