Effects of vibrating and deformed trailing edge of a morphing supercritical airfoil in transonic regime by numerical simulation at high Reynolds number

Abstract

This article examines the aerodynamic performance increase of an Airbus A320 aerofoil thanks to morphing of the near-trailing-edge region in transonic regime corresponding to cruise conditions. The study has been carried out by numerical simulation at Reynolds number Re = 2.06 × 10 6 and Mach number of 0.78, by using the NSMB code (Navier-Stokes MultiBlock) including adapted turbulence modelling approaches sensitised in capturing coherent structures development.

CFD simulations of active flow control devices applied on a cambered flap

“…For unsteady CFD simulations Hybrid RANS-LES models are available as well as the k-𝜖 Organized Eddy Simulation model [20,21] which were used for 2D and 3D simulations. The Arbitrary Lagrangian Eulerian (ALE) approach is employed for simulations using moving or deforming grids employed in morphing simulations ( [22,23]). NSMB includes a re-meshing algorithm that is a combination of Volume Spline Interpolation (VSI) [24] and Transfinite Interpolation (TFI).…”

Flow analysis around a VTOL aircraft near stall conditions and application of Active Flow Control to enhance the aerodynamic performances at real flight conditions

“…NSMB solves the Reynolds-averaged Navier Stokes equations for compressible flows on multi-block structured grids. NSMB offers all functionalities of a modern CFD code used for aerospace applications, among others, ALE (Arbitrary Lagrangian Eulerian) approach [18], turbulence models [19], chemistry modelling, grid flexibility, FSI (Fluid-Structure Interactions) coupling such as morphing wings modelling ( [20][21][22]), Chimera overlapping technique [23]. Space discretization schemes include 2nd-and 4th-order central schemes with artificial dissipation and various upwind schemes (Roe, AUSM, Van Leer ...) up to 5th order.…”

“…NSMB includes also a large variety of well tested and validated turbulence models that are standard in the aeronautical industry, like the one-equation Spalart-Allmaras [24], the Organized Eddy Simulation model [19,25], or the two-equation by Menter [26], that have been applied in the present study. Different morphing concepts are also implemented [13,[27][28][29][30] in the code. Unsteady simulations are made using the dual time stepping approach or using Newton's approach.…”

Computational analysis and design of an aerofoil with morphing tail for improved aerodynamic performance in transonic regime

“…Furthermore, a relatively low deflection range has been used in order to avoid massive boundary layer detachment after the shock wave. Moreover, Tô et al [46] suggests that the designs of the morphing part should be able to slightly deflect in order to avoid aeroelastic instabilities such as buffeting. Finally, the range of morphing location has been chosen to be similar to the studies carried out by other authors (e.g.…”