The application and workflow of Computational Fluid Dynamics (CFD)/Computational Structure Dynamics (CSD) on solving the\nstatic aeroelastic problem of a slender rocket are introduced. To predict static aeroelastic behavior accurately, two-way coupling\nand inertia relief methods are used to calculate the static deformations and aerodynamic characteristics of the deformed rocket.\nThe aerodynamic coefficients of rigid rocket are computed firstly and compared with the experimental data, which verified the\naccuracy of CFD output.The results of the analysis for elastic rocket in the nonspinning and spinning states are compared with the\nrigid ones. The results highlight that the rocket deformation aspects are decided by the normal force distribution along the rocket\nlength. Rocket deformation becomes larger with increasing the flight angle of attack. Drag and lift force coefficients decrease and\npitching moment coefficients increase due to rocket deformations, center of pressure location forwards, and stability of the rockets\ndecreases. Accordingly, the flight trajectory may be affected by the change of these aerodynamic coefficients and stability.
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