Abstract: The high-speed deploying procedure of folding wing of an aircraft was simulated, with both steady and unsteady numerical method, to study its aerodynamic loads. The aerodynamic characteristic during the deploying process, including the influences of the deploying angle and the incoming flow parameters on the aerodynamic loads on the wing, was resolved by steady numerical simulation. The unsteady numerical approach was applied to study the unsteady characteristic by obtaining and comparing the aerodynamic loads under various angular velocities. It is found that when the deploying velocity is comparable to the freestream velocity, the unsteady effect is not negligible.