Abstract
An important aspect of aeroservoelasticity is the analysis of interactions between rigid, elastic, and control modes. The stability and control derivatives were determined for a high number (90) of flight test conditions expressed in terms of Mach number, altitudes, and angles of attack. In this paper, the rigid and control mode aerodynamic forces for an F/A-18 aircraft are calculated and validated by two methods (numerical and analytical). The results obtained here were found to be identical for all flight test conditions.
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