Dynamic characteristics of a missile wing can changes largely because o f the thermal effect during a hypersonic flight. A thickness variable wing model is analyzed by the finite element method (FEM) to obtain its dynamic characteri stic and temperature field changes under heating. The result of FEM are compared with that of the experiment, which shows that the natural vibration frequencies will decrease with the material elastic modulus changes and the thermal stresse s generation along with the aerodynamic heating. The change of material elastic modulus affects the natural frequencies much more than the thermal stress does. In the experiment, when the temperature of the wing’s surface increases by 190 degrees Celsius, the first three natural frequencies have a maximum decrease of 13 percent.