Experimental and Numerical Investigation of a Circulation Control Airfoil

Pfingsten, K. C.; Radespiel, Rolf

doi:10.2514/6.2009-533

Cited by 44 publications

(15 citation statements)

References 5 publications

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“…To avoid flow separation due to the strongly bend flow, a high speed tangential blowing is realized on the flap. This effect was first described by Coanda 2 and has since been successfully simulated and tested in wind tunnels 3 In 2010, Pott-Pollenske and Pfingsten 5 showed experimentally that with such a circulation control airfoil significant noise reduction in the frequency range of 2 to 20 kHz on model scale can be achieved compared to a classic 3 element high lift airfoil with slotted slat and flap. However, in the lower frequency domain a noise increase was found.…”

Section: Introductionmentioning

confidence: 93%

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: Introductionmentioning

confidence: 93%

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 characteristic is fundamental for the simulation of the Coanda phenomenon, which is based on the equilibrium between the inertial forces and the momentum transport in the direction normal to the convex surface [28]. The numerical scheme and the turbulence model were previously assessed by comparing the results to wind tunnel experiments [29,30]. The lift, drag, and pitching moment coefficients are determined by integrating the pressure and shear stress distributions over the airfoil surface.…”

Section: Unsteady Reynolds Averaged Navier-stokes Simulationsmentioning

confidence: 99%

Optimal sensor placement using machine learning

Semaan

2017

Computers & Fluids

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A new method for optimal sensor placement based on variable importance of machine learned models is proposed. With its simplicity, adaptivity, and low computational cost, the method offers many advantages over existing approaches. The new method is implemented on the flow over an airfoil equipped with a Coanda actuator. The analysis is based on flow field data obtained from 2D unsteady Reynolds averaged Navier-Stokes (URANS) simulations with different actuation conditions. The optimal sensor locations is compared against the current de-facto standard of maximum POD modal amplitude location, and against a brute force approach that scans all possible sensor combinations. The results show that both the flow conditions and the type of sensor have an effect on the optimal sensor placement, whereas the choice of the response function appears to have limited influence.

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“…Yet, the greater part of this work concentrates on aerodynamic aspects of lift gain in a steady-state flow, e.g. [1][2][3][4]. The aeroelastic behaviour of an aerofoil including circulation control is not fully understood.…”

Section: Introductionmentioning

confidence: 99%

Flutter of circulation-controlled wings

Dinkler

Krukow

2015

CEAS Aeronaut J

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The application of active circulation control gives rise to a substantial increase in lift compared to conventional wings. Initial studies of the aeroelastic behaviour of a circulation-controlled wing have shown additional instabilities due to the active circulation control. Besides the heave flutter phenomenon, further investigation also reveals a destabilising effect of the aerodynamic derivatives related to pitch, which is peculiar to circulationcontrolled wings. The goal of the present paper is to investigate these phenomena in detail.

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Experimental and Numerical Investigation of a Circulation Control Airfoil

Cited by 44 publications

References 5 publications

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

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

Optimal sensor placement using machine learning

Flutter of circulation-controlled wings

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