High-accuracy static aeroelastic analysis of fighter's transonic aileron efficiency and test flight verification

The transonic aileron efficiency is a hotspot and difficulty in the field of static aeroelastic analysis. The computational fluid dynamics (CFD)/computational structural dynamics (CSD) interaction method can supply high-accuracy resolutions, but it still has problems of mesh deformation robustness and lack of verification. Aimed at the above issues, a new method of mesh deformation based on dummy grids and dummy deformation was developed, and for the problems of non-physical oscillation and non-uniformly convergence in the process of interaction, the lax iteration method and comprehensive residual criterions were used. Based on the methods, the transonic (Ma=0.95) aileron efficiency of a fighter was analyzed, and the shock position/strength and the pressure distribution due to the static aeroelastic deformation were presented. The ration of elastic and rigid aileron efficiency was compared to the results of flight identification, which proves that the methods can meet the requirement of high-accuracy analysis for transonic static aeroelastic problems of control surfaces. The methods are of great significance for static aeroelastic engineering design capability enhancement.