Application of the finite element technique to aerodynamic problems of aircraft

Abstract Finite element techniques combined with the collocation method are formulated and applied to obtain numerical solutions for the integral equation which determines the airload acting on the wings, body and other components of an aircraft. In the first part, the aerodynamic interaction problems of wings and a body are studied by a finite element method based on Morino's method. Examples include the steady airloads over cross wings with or without a fillet, and a wing-lifting body combination. In the last part, the lifting surface problems are solved for the airloads by the finite element technique employing triangular or quadrilateral elements, where the conditions that the shape functions must satisfy are emphasized. Examples include not only the steady airload over a rectangular wing with partial-span flap, but also the unsteady airload over a rectangular wing oscillating in the first bending mode.

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