Flowfield measurements about a multi-element airfoil at high Reynolds numbers

Chin, Vincent; Peters, David W.; Spaid, Frank W.; McGhee, Robert

doi:10.2514/6.1993-3137

Cited by 105 publications

(49 citation statements)

References 2 publications

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“…They also showed a considerable increase in the maximum lift between Re c = 2 × 10 6 and 9 × 10 6 at a Mach number of 0.2. The effects of Reynolds number and its significance on lift of high-lift airfoil was also showed by Chin et al [24] and they also discussed the increased effect of Reynolds number on the suction peak of the flap. The pressure distribution with respect to model the coordinates for the Baseline case at the tested angles of attack α = 6…”

Section: Pressure Coefficient Distributionmentioning

confidence: 70%

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%

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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“…This is because the data for the two-segment flap is used for the current figure. Careful inspection of figures 12 and 14 indicates that differences in the experimentally obtained lift between the one-and two-segment flap appear to start at about 20 . This difference may be due to slight differences in the model geometry or because the flow may no longer be two dimensional at this angle of attack.…”

Section: Resultsmentioning

confidence: 99%

“…The test data is the result of a cooperative experimental program between the Douglas Aircraft Company and the NASA Langley Research Center and is reported in references [19] and [20]. Test Reynolds numbers varied between 5, 9, and 16 million.…”

Section: Experimental Datamentioning

confidence: 99%

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Navier-Stokes computations and experimental comparisons for multielement airfoil configurations

Anderson

Bonhaus

McGhee

et al. 1995

Journal of Aircraft

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“…It has the advantage of highly convergence criteria and high mesh topology. The multi block unstructured grid is used for multi element airfoil with fine mesh using sphere of influence method [6][7][8][9][10].…”

Section: Numerical Methods and Meshmentioning

confidence: 99%

Aerodynamic Analysis of Multi Element Airfoil

D¹,

S²

2016

J Aeronaut Aerospace Eng

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The flow over multi-element airfoils has been numerically investigated in ANSYS fluent and has been compare the aerodynamic parameters with the standard NACA airfoils 4412 and 0012. The 2D viscous, transient, pressure model equations together with the k-ω turbulence model were applied to this numerical simulation utilizing the multiblock unstructured grids of sphere of influence type. Numerical results showed that the aerodynamic parameters of multi element airfoils with tail effect are much optimum than the standard NACA airfoils. Also the analysis is made on different flap and slat angles of different conditions and the optimization of multi element airfoils has been performed.

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Flowfield measurements about a multi-element airfoil at high Reynolds numbers

Cited by 105 publications

References 2 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

Navier-Stokes computations and experimental comparisons for multielement airfoil configurations

Aerodynamic Analysis of Multi Element Airfoil

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