Aeroelastic simulations of the SADE FNG smart leading edge - smart single slotted flap high-lift configuration

摘要

The scope of this paper is to show the result from the evaluation of aeroelastic efficiency of the FNG high-lift configuration, investigated within the EU-project SADE. The CAD geometry of the FNG wing was provided by DLR. A CFD mesh was generated by FOI. The initial MSC-NASTRAN structural finite element (FE) model was produced by VZLU. This model was then used for further structural aeroelastic optimisation (FOI) and an evaluation of the aeroelastic efficiency using both standard engineering methodology and more advanced CFD based fluid-structure coupled analysis. In the optimization, regions of the vehicle where weight reduction seems possible were identified and the gain was determined. The constraints in the optimization include: static strength, structural stiffness, flutter damping and control surface authority. The results from the optimization indicate a potential for weight reduction of almost 1 ton, or 12% of the initial weight. Finally, a structural coupled CFD analysis was carried out using the Edge CFD solver, with a built-in linear structural solver. The mode shape for the structure was obtained from using MSC-NASTRAN and projected to the CFD surface mesh. The sharing of forces and displacement is done at every time step and followed by online mesh deformation. The static aeroelastic result using panel method is qualitatively compared with CFD. The result also demonstrates the possibility to use structural aeroelastic optimisation and high fidelity CFD methods in the evaluation of aeroelastic performance on a realistic and rather complicated case.