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Unformatted text preview: c Nomenclature air density W aircraft weight S reference area (wing area) b wing span I average wing chord taper ratio AR wing aspect ratio o wing root bending inertia E Youngs modulus c C P P g gravity elec electric power max maximum thrust power ( = ( P elec ) max ) overall propulsive eciency L lift coecient d wing profile drag coecient CDA 0 drag area of non-wing components airfoil thickness/chord ratio tip deection Assumed Design Variables The primary design variables here are assumed to be AR and S . Other design variables such as , , etc., may also be considered, although for brevity these will not be shown in the argument lists below. The following dependent auxilliary functions and constraint functions are assumed to be known from suitable analyses: c ( AR, S ) = S/AR (1) b ( AR, S ) = S AR (2) W wing ( AR, S ) = . 6 c 2 b foam g (3) W ( AR, S ) = W wing + W fuse (4) 2 4 4 I ( AR, S ) = . 04 3 c (5) W 1+ fuse b 2 1+2...
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.
- Fall '05