Experimental Investigation of Flow Around Three-Element High-Lift Airfoil with Morphing Fillers

Abstract

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.

Aerodynamic and Aeroacoustic Performance of Airfoils Fitted with Morphing Trailing-edges

“…As such, airfoil self-noise has been considered as an important component of airframe noise during take-off and landing. Some of the currently employed passive methods for airfoil trailing edge noise reduction includes serrated trailing edges [3,4], porous surface treatments [5][6][7][8] and morphing trailing edges [9][10][11][12]. With the use of morphing surfaces our aim is to address transition delay, separation postponement, lift enhancement, drag reduction, turbulence augmentation and noise suppression [13].…”

Aerodynamics of the turbulent flow around a multi­element airfoil in cruse configuration and in takeoff and landing configuration

“…Only small angles of attack were considered: 4°, 5.5°, 8.5°. The Reynolds number was 1.6×10 6 , which is an order of magnitude less than the values corresponding to actual wings.…”

“…Mathematical modeling of the turbulent flow around multi-element airfoils is a rather difficult task of computational aerodynamics [4,5]. Many publications in the modern scientific literature attempt to solve this problem [6][7][8][9][10][11][12][13].…”

“…Paper [6] reports an experimental study into the flow around the three-element aerodynamic airfoil 30P30N for cruise configuration in the range of Reynolds numbers from 4.6×10 5 to 1.1×10 6 and the angles of attack from 0° to 12°. The authors give the distributed aerodynamic airfoil characteristics.…”

Airfoil Trailing-edge Noise Reduction using Flow Suction

“…For Passive flow control approach, no external energy is added to alter the boundary layer. The changes to the flow characteristics are introduced by adding devices like serrations [2][3][4][5], types of riblets, morphing [6][7][8][9][10] or by applying porous [11][12][13] and compliant materials. whereas, for the active flow control method [14] external energy is added to the flow.…”