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The aerodynamic features of the C-5A discussed will include only those items which posed a significant challenge to the aerodynamicist: airfoil sections, high lift systems, and control and augmentation systems. While the cruise configuration is quite conventional in that the C-5A uses a moderately swept wing, a tee-tail, and wing-pylon-mounted engines, the design requirements for forward and aft straight-in fuselage loading coupled with the provision of personnel accommodations, airdrop capability, and extremely high flotation, dictated fuselage and landing gear configurations which required an intensive effort to reduce aerodynamic drag to an absolute minimum level. This effort will be discussed. The design of the high lift system was dictated by extremely stringent airport requirements and the high wing loading necessary to achieve optimum matching of airframe and engine in the cruise regime.

The Lockheed C-5 is unique with respect to size, pay-load/range, and engine thrust rating. The upper deck, contains the passenger carrying compartments, although the cargo compartment, when properly supplemented, may also be used for emergency evacuation of troops. Comfortable accommodations, along with galley and sanitation facilities, are provided for crew, relief crew, and troops. Operational aspects of the cargo handling subsystem are multiple and varied. Sophisticated procedures accomplish the primary logistics mission of loading, restraining, and unloading of vehicular, bulk, and palletized cargo. The C-5 has the additional facility for aerial delivery of cargo and troops.