12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference) 2006
DOI: 10.2514/6.2006-2562
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Low Noise Design Trends Derived from wind tunnel Testing on Advanced High-Lift Devices

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Cited by 9 publications
(8 citation statements)
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“…An efficient high lift system that produces a high maximum lift coefficient generally has a high noise signature (e.g. multi-slotted flaps and slats) (Bertsch, 2013), (Pollenske, 2014, Fischer, 2006. Figure 3 shows that a wing loading of 450 kg/m² would not only lower the Maximum Take-off Weight (MTOW) by 2 % compared to a wing loading of 350 kg/m², but also increases the Specific Air Range (SAR) by 6.2 %.…”
Section: Figurementioning
confidence: 99%
“…An efficient high lift system that produces a high maximum lift coefficient generally has a high noise signature (e.g. multi-slotted flaps and slats) (Bertsch, 2013), (Pollenske, 2014, Fischer, 2006. Figure 3 shows that a wing loading of 450 kg/m² would not only lower the Maximum Take-off Weight (MTOW) by 2 % compared to a wing loading of 350 kg/m², but also increases the Specific Air Range (SAR) by 6.2 %.…”
Section: Figurementioning
confidence: 99%
“…A final application of morphing technology by using deformable surfaces is noise reduction. It is known that major acoustic sources are located at surface discontinuities (slat and flap ends, see Reference [12]) and the use of a continuous surface will suppress the noise emission at these locations. For instance, tests carried out by NASA on a business jet configuration (Figure 6) will certainly show significant noise reduction when compared with the reference plane.…”
Section: Introduction: the Different Uses Of Morphing Technology Fmentioning
confidence: 99%
“…Turning now to slat noise reduction devices, several concepts such as trailing edge serration, comb-like trailing edge, and slat cove filler (SCF) seem to be effective candidates [16]. Other approaches, such as adjusting distribution of aerodynamic load shared among each wing element have been also suggested [17]. However, we still do not clearly understand the relation between noise generation and flow physics, and further knowledge is necessary for reducing noise in actual flight condition.…”
Section: Introductionmentioning
confidence: 99%