Numerical Study of Trailing-Edge Dynamics of a Two Element Airfoil-Flap with Morphing Flap at High Reynolds Number

摘要

This article examines the morphing effect of trailing-edge flap of high lift configuration at the take-off position. It includes vibrations with different frequencies and amplitudes around the supercritical Airbus A320 wing-flap. The Reynolds number is 2.25 million and the angle of attack 8.2° which corresponds to take-off and landing phases. The flap deflection angle from its initial position is 10° and translated with 30 cm horizontally from the main wing. The results have been validated with numerical data that worked on a similar two-element wing named GA (W) 2. In the present study, we show through spectral analysis and Proper Orthogonal Decomposition (POD the influence on the wake's width and on the aerodynamic performances, on the predominant frequencies and instabilities.