Aeroacoustic Performance of an Airfoil with Circulation Control

Pott-Pollenske, Michael; Pfingsten, K. C.

doi:10.2514/6.2010-3881

Cited by 6 publications

(3 citation statements)

References 11 publications

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“…It can be clearly seen, that the case with flow separation produces much more low-to mid-frequency sound, which conforms with the expectations from earlier measurements. 5 Furthermore, for frequencies above about 8 kHz the difference vanishes. This nicely shows the importance of getting the right flow when comparing simulation results to measurements on the one side and the acoustic impact of aerodynamically acceptable partial flow separation on the other side.…”

Section: Ivb1 Simulationmentioning

confidence: 95%

Numerical and experimental insights into the noise generation of a circulation control airfoil

Rossian

Suryadi

Rossignol

et al. 2018

2018 AIAA/CEAS Aeroacoustics Conference

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With the advances in reduction of propulsion related noise from aircraft, airframe noise gets more and more into focus. During approach and landing, the high-lift system of the wings becomes one major acoustic source region contributing to the overall emitted noise. One promising approach to reduce this airframe noise is to change the complete high-lift system from a classic three element slat-wing-flap configuration to a slot-less system with active blowing and droop nose. Preceding experimental investigations have shown, that such a configuration may provide a noise reduction above 2 kHz on the model scale. In the present paper both numerical and experimental investigations concerning the acoustics of a high-lift wing with droop nose and active blowing are presented. Thereby, an insight into the acoustic source mechanisms for different aerodynamic setups is provided that in the future will serve as a basis for the design of a low-noise high-lift configuration. It was found, that in principle three source mechanisms are to be considered. In the low to mid frequency domain, mostly turbulence-geometry interaction noise such as trailing edge noise, jet-nozzle interaction noise and curvature noise from the flow being bent around the flap are supposed to be the driving mechanisms. Moreover, the high frequency domain is found to be dominated by mixing noise from the high speed jet. NomenclatureA = wing area [m 2 ] b = wing span [m] c = chord length [m] c µ = jet momentum coefficient h = height [m] m = mass flow kg s M a = Mach number p = pressure [Pa] Re = Reynolds number R s = specific gas constant J kg K T = temperature [K] U = scalar velocity magnitude m s

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Section: Ivb1 Simulationmentioning

confidence: 95%

Numerical and experimental insights into the noise generation of a circulation control airfoil

Rossian

Suryadi

Rossignol

et al. 2018

2018 AIAA/CEAS Aeroacoustics Conference

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“…This is a rough estimation but is based on findings in the literature. 68,69,70,71,10 The initial noise assessment of the REF3 aircraft in Ref. 67 indicates that for a continuous descent approach the high-lift system may not be the dominant noise source.…”

Section: Coanda Flapmentioning

confidence: 99%

Aircraft and technology for low noise short take-off and landing

Delfs

Appel

Bernicke

et al. 2017

35th AIAA Applied Aerodynamics Conference

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This paper discusses characteristic multidisciplinary issues related to quiet short takeoff and landing for civil transport aircraft with a typical short to medium range mission. The work reported here is focussing on the noise aspects and is embedded in the collaborative research centre CRC880 in Braunschweig, Germany. This long term aircraft research initiative focusses on a new transport aircraft segment for operation on airports with shorter runway length in commercial air transport. This calls for a community-friendly aircraft designed for operations much closer to the home of its passengers than today. This scenario sets challenging, seemingly contradictory aircraft technology requirements, namely those for extreme lift augmentation at low noise. The Research Centre CRC880 has therefore devised a range of technology projects that aim at significant noise reductions and at the generation of efficient and flexible high lift. The research also addresses flight dynamics of aircraft at takeoff and landing. Two companion papers, reporting about the research in the field of "Efficient high lift" 1 and "Flight dynamics" 2 complete the presentation of the CRC880. It is envisaged that in general significant noise reduction-compared to a reference turbofan driven aircraft of year 2000 technology-necessarily requires component noise reduction in combination with a low noise a/c concept. Results are presented from all the acoustics related projects of CRC880 which cover the aeroacoustic simulation of the source noise reduction by flow permeable materials, the characterization, development, manufacturing and operation of (porous) materials especially tailored to aeroacoustics, new UHBR turbofan arrangements for minimum exterior noise due to acoustic shielding as well as the prediction of jet noise vibration excitation of cabin noise by UHBR engines compared to conventional turbofans at cruise.

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“…Increased lift coefficients reduce takeoff and landing speeds and distances, or reduce control surface area. Previous active lift studies 5,6,7 have considered unswept, constant chord configurations with trailing-edge blowing. The present investigation was undertaken to characterize the aerodynamic and aeroacoustic performance of a full-span flight configuration with integrated trailing-and leadingedge slot blowing and over-the-wing turbine propulsion simulators.…”

Section: Introductionmentioning

confidence: 99%