An airplane has been planned to be used for Mars exploration. The wing folding technology for such an airplane has been paid attention to because it offers a large wing area to get enough lift force and compactness for transfer to Mars. In addition, aerial deployment allows for using the initial altitude to its advantage. However, aerial deployment motion is complex and has a possibility of failure. This paper presents the result of a numerical analysis for the aerial deployment motion of a folded-wing airplane. The requirements for successful aerial wing deployment were defined. The sensitivity analysis results are evaluated using the requirements. Successful input range, and lower and upper constraints are revealed. The most sensitive requirement is the hinge reaction moment. Successful combinations among a spring, a damper, and aerodynamic force for the safe aerial deployment were quantitatively obtained.