Transonic aeroelasticity design method with application to a wing

Abstract The transonic region is the most serious aeroelastic stability problem due to the existence of nonlinear factors such as shock waves, and it has been troubling the design and research of aircraft for a long time. In this paper, according to the characteristics of different design stages of aircraft, a transonic aeroelastic design method is proposed to balance the requirements of calculation accuracy and efficiency. This method analyzes the transonic flutter characteristics of an ultra-thin wing. In the preliminary design stage, a transonic flutter analysis method based on the correction of steady aerodynamic coefficient is proposed. This method is more accurate than the linear flutter analysis method in engineering while maintaining high efficiency and can calculate the transonic pitting phenomenon of wing flutter velocity. In the flutter evaluation stage of different structural schemes, the demand for accuracy and accuracy is greatly improved. Although the aerodynamic response obtained by computational fluid dynamics (CFD)/computational solid mechanics (CSD) coupling numerical simulation method and wind tunnel test provide rich details, the efficiency is low. Therefore, a time-domain fluid structure coupling flutter analysis method based on CFD and modal method is proposed. The flutter check of the wing is carried out by the time-domain fluid-structure coupling flutter analysis method, and it is found that the wing does not flutter under all required conditions, which meets the design requirements.