The overset field-panel method presented solves the integral equation of the time-linearized transonic small disturbance equation by an overset field-panel scheme for rapid transonic aeroelastic applications of complex configurations. A block-tridiagonal approximation technique is developed to greatly improve the computational efficiency to solve the large size volume-cell influence coefficient matrix. Using the high-fidelity computational-fluid-dynamics solution as the steady background flow, the present method shows that simple theories based on the small disturbance approach can yield accurate unsteady transonic flow predictions. The aerodynamic influence coefficient matrix generated by the present method can be repeatedly used in a structural design loop, rendering the present method as an ideal tool for multidisciplinary optimization.
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Chen et al. (2004) studied this question.
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