Abstract: The elastic forces and aerodynamics loads coupling effects are important or determined in transonic regime of the military aircraft operation and military subsonic transports. The aero industries compulsorily need the areoelastic effect for design the aircraft. The aero industries are computationally interaction of predicts. For analysing the air craft wings the CFD tool is used when fidelity is more. And the CSD tool is used to analysis when aerodynamic behaviour is non linear. For find the aeroelastic effect there are various methods available in CSD and CFD. By using this two methods there is no need of source codes alteration. In other tools they need the source codes for analysis the aircraft wings. In this study, aircraft wings are developed for aeroelastic response by using the coupling procedure. The little code integration of CSD and CFD tools are used here. The NASTRAN and NASTD procedure used to demonstrate the F/A-18 stabilator. The wing box code was additionally coupled by the NASA. The both results modal super position and NASA are obtained by the study. Finally, the experimental data is compared with the results.