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This paper introduces a method for computing static and dynamic stability derivatives of aircraft using a three-dimensional computational fluid dynamics (CFD) approach combined with an automatic differentiation adjoint (ADjoint) technique. The method effectively simulates flow characteristics around arbitrary aircraft configurations, allowing for efficient and accurate calculations of stability derivatives, demonstrated through examples like the NACA 0012 airfoil and ONERA M6 wing. The approach aims to enha
- Author
- toolpost
- Language
- EN