Experimental and numerical investigation of aerodynamic performance for airfoils with morphed trailing edges

Abstract

The aerodynamic performance of a NACA 0012 airfoil with morphing flaps were studied experimentally and numerically. Comprehensive aerodynamic measurements including pressure distribution, lift and drag forces and wake flow for airfoils with different morphing flap camber profiles were carried out over a wide range of angles of attack and chord-based Reynolds numbers. The results show that the morphing flap camber profiles significantly affect the aerodynamic performance and the downstream wake development. It was found that the highly cambered flap profiles provide higher lift coefficients compared to the moderately cambered flap profiles, with an insignificant reduction in the overall lift-to-drag ratio. Furthermore, the Q-criterion iso-surface results show

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

“…Complimenting the previous study [12] the current experimental and numerical study investigates aerodynamic and aeroacoustic behavior for a morphed and hinged airfoil with a trip. This paper presents a detailed aerodynamic study with lift and drag measurements, surface flow visualization, Particle Image Velocimetry.…”

“…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].…”

“…Most of the studies showed much interest on than the morphing structures and mechanism [14][15][16][17][18][19][20] than the aerodynamic and aeroacoustic performance. An innovative trailing-edge morphing mechanism that uses a honeycomb core with axial variable stiffness developed by Ai et al [19,20], was used as morphing profile for the experimental and computational studies carried out by Jawahar et al [10][11][12]. The recent study Jawahar et al [12] showed that small changes in the flap camber profile of the morphed flap can change the aerodynamic behaviour significantly.…”

“…An innovative trailing-edge morphing mechanism that uses a honeycomb core with axial variable stiffness developed by Ai et al [19,20], was used as morphing profile for the experimental and computational studies carried out by Jawahar et al [10][11][12]. The recent study Jawahar et al [12] showed that small changes in the flap camber profile of the morphed flap can change the aerodynamic behaviour significantly. The lift and drag were shown to be affected with flap with higher camber producing larger lift but with higher drag.…”

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.…”