This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Aerodynamic Design Features of the C-5A
Annotation ability available
Sector:
Language:
English
Abstract
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. In addition, the use of a modest thrust-to-weight ratio, coupled with a high thrust lapse rate with speed aggravated the difficulties associated with development of a suitable high lift system. The methods used to achieve the necessary aerodynamic high lift system performance while satisfying structural requirements are discussed.
Recommended Content
Technical Paper | Observations and Analyses of Natural Laminar Flow over a Nonlifting Airframe Surface |
Technical Paper | Drag Analysis Methods for Light Aircraft |
Technical Paper | Wind Tunnel Investigations of a High Speed Stowed Rotor Aircraft |
Citation
Paterson, J., "Aerodynamic Design Features of the C-5A," SAE Technical Paper 670847, 1967, https://doi.org/10.4271/670847.Also In
References
- Pearcey H. H. “ The Aerodynamic Design of Section Shapes for Swept Wings.” Advances in Aeronautical Sciences 3 277 322
- Taylor R. T. Ray E. J. “ Deep Stall Aerodynamic Characteristics of T-Tail Aircraft.” NASA Conference on Aircraft Operating Problems May 1965
- Shevell R. S. Schaufele R. D. “ Aerodynamic Design Features of the DC-9.” Journal of Aircraft 3 6 515 523
- Byrnes A. L. Hensleigh W. E. Tolve L. A. “ Effect of Horizontal Stabilizer Vertical Location on the Design of Large Transport Aircraft.” Paper 65-331 presented at AIAA Second Annual Meeting San Francisco Jul. 1965