Title: Trim Equations of Motion for Aircraft Design: Steady State Straight Line Flight
Abstract: NOMENCLATURE The development of performance-optimal stability and control design solutions for advanced conventional and unconventional aircraft configuration shapes pose a particular challenge during the conceptual design phase. This design challenge can be attributed to a lack of design methods available, chronic data shortage when dealing with novel configuration shapes, and permanent time pressure during the early conceptual design segment. The situation is particularly apt when evaluating symmetric or asymmetric aircraft shapes in asymmetric flight conditions. b = span D C = drag coefficient (aircraft) 0 D C = drag coefficient (aircraft) for zero angle-of-attack α D C = variation of aircraft drag coefficient with angle of attack l
Publication Year: 2003
Publication Date: 2003-06-22
Language: en
Type: article
Indexed In: ['crossref']
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Cited By Count: 15
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