Static aeroelasticity analysis method of civil aircraft under powered condition

Based on the N-S equations of multi-block structural grid and the method of structure flexibility coefficient matrix, an approach to CFD/CSD non-linear coupling problem based on radial basis functions(RBF) interpolation technology is established, RBF&Delaunay mesh motion method is adopted, which is used to compute the non-linear aeroelasticity of flexible aircraft with high aspect radio. This method is validated using DLR F6 configuration simulation. According to this method, static aeroelasficities of a civil aircraft under no jet/jet condition are investigated, showing that the engine jet can make wing plus twist, which is weaken wing sweepback effect, then the leading and trailing edge bending deformation increase and most of the favorable current profile twist angles decrease. Studies show that under the powered condition, the pressure distribution of rigid wing is changed, its lift confficient is reduced. The static aeroelastic deformation is a coupling effect, where the engine jet region is mainly influenced by jet while the outer wing is mainly by elastic deformation. The result of numerical simulation demonstrates that considering the aeroelasticity effect for no jet condition, the lift coefficient decreases by about 16% and the lift drag radio decreases by 8.4%. Whereas for powered case, the lift coefficient decreases by 18%, the lift drag radio decreases by 36%. Therefore, it is necessary to analyze static aeroelasticity of high aspect radio civil aircraft under powered condition.