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Unformatted text preview: to note that EDA= for the case of a simple Vdihedral wing with constant ( ). By introducing the cubedellipse function f = 1 2 3 / 2 (2) df = 3 1 2 1 / 2 d (3) equation (1) can be rewritten as follows. 0 EDA = df (4) 1 For the usual case where the wing consists of at panels, is piecewise constant, with values 1 , 2 . . . in between the dihedralbreak stations , 1 , 2 . . . . The integral (4) can then be written as a sum over the individual panels. The 2panel case is shown in Figure 1. EDA = 1 ( f 0 f 1 ) + 2 ( f 1 f 2 ) + . . . (5) f 1 f 1 f 2 f f 1 0 1 2 1 2 = 0 1 2 = 1 1 2 Figure 1: Quantities used for calculating the EDA of a 2panel polyhedral wing....
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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
 MarkDrela

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