Abstract: In conventional force measure wind tunnel test,the balance can get the aerodynamic force of the aircraft and also the directly moment . It is while the pressure center is usually considered as the intersection point between aerocraft's longitudinal axis and its aerodynamic force, which is not the virtually real value of the pressure center of the aircraft. How to obtain the pressure center of re-entry aerocraft accurately with the general method in wind tunnel test remains a difficult problem. In this paper, the position of re-entry vehicle’s pressure center was obtained through the technique of attack angle continuous change and real-time data acquisition. Also the pressure center of re-entry module change rule with the change of attack angle was obtained. Experiments demonstrated the feasibility of the proposed method. With the increasing of negatives attack angle, the contribution of axial force to pitch moment becomes great, while the influence of normal force is just the contrary, which results in thickcreased gap between the conventional measured value and the real value of vehicle’s center of pressure. The vertical position of re-entry aircraft’s load center is relatively small in the test. The final CACm curve shows that the axial force CA should not be neglected or simplified in wind tunnel test.