The unsteady aerodynamicals and areoelastic stabilities of wings with oscillating control surface and external store investigated in the transonic and supersonic flow region. The TSD3KR code based on the transonic small distribance theory has been develoed to calculate the steady and unsteady aerodynamic forces. Good correlations with the wind tunnel test results were found for various wing configurations. The present flutter analysis system based on the modal approach includes the numerical interpolation and unsteady aerodynamic analysis modules. The analysis system has the analytical capability in both the frequency and the time domain. The analyses of the three different wing models with the experimental wind-tunnel flutter test data have been performed to validate the present flutter analysis system. A wing-box structural model of fighter type wing is created to show the realistic characteristics of structural vibration and flutter responses. From the results of present study, it is shown that the rotation stiffness of control surface gives dominant effects for the flutter stability In the case of wing external store, the aeroelastic responses of wing show more unstable characteristics such as limit cycle oscillation and chaotic motion at Mach 0.95∼1.1, where the aerodynamic nonlinearities due to strong shock motion are highly expected.
