From the perspective of aircraft wing-box lectotype design, the capability of honeycomb core sandwich form and the stiffener panel form are compared based on the same weight structure. Through engineering calculations, the two forms are respectively analyzed about their resistance against compression buckling and bending stiffness. Data results are charted about different laminate thickness, stiffener spacing, and profile height. The comparison can deducted that sandwich form should have higher priority over stiffener form when laminate is thin and wing-box is low, which appears on movable surfaces such as flap and aileron. On the other hand, when it comes to outboard wing and central wing where laminate is thick and wing box high, stiffener form is more structural efficient.