The flutter analysis of a supersonic flight vehicle has been investigated. The third order piston theory has been applied for the aerodynamic analysis and the finite element method has been used for the structural analysis. The flutter solution has been obtained by using V-g method. The surface spline method is used for the interpolation between structural and aerodynamic grid points of the wing. The linear spline method is used for body of the flight vehicle. The effects of the wing thickness and body on the flutter are investigated. The flutter speeds decrease when the body is included in the flutter analysis model. The effect of body aerodynamics on the flutter is very small. The developed computer program gives quite accurate results compared with the existing results.
