Abstract
This chapter describes how lift can be derived from a known aircraft geometry and conversely, how the selection of aircraft layout influences the generation of lift. As the fuselage shape is predetermined by the payload requirements, the nacelle geometry by the engine size, and the tail surfaces by stability considerations, the wing parameters are the principal variables to be considered in respect to lift aspects. To this end, guidance is given on the selection of wing section profile and platform geometry to provide specified performance requirements. A lift estimation method covering all the aircraft components is also provided. Such methods are suitable for use in the conceptual design phase and provide an introduction to more detailed estimation procedures.
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