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ence between adjacent wing sections. Thus, the strip theory predictions will be in
error for wings with small aspect ratio. For more accurate prediction of (Clr)W at
subsonic speeds, the following Datcon/ formula can be used:
where
(CLr)W=C,(g),,=O.At+(~-)r7rad (4.613)
                                 ' (4.614)
(g ).,=o.)w = NDe  (g ).,=O,M=O
                                      A(l - B2)                            + 2 cos A,
Num -l+2B AB+2  osA~4 +(~~~4,os~ t)(_a 8At )
           (4.615)
Den-.l+ ~:j::~/)( 8A )    (4.616)
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 415
SUBSONIC SPEEDS
Ac/4 (deg)
TAPER
RATIO
0   15    30       45         60             x
                                                                                                                             
                                                                                                                             
                                                                                                                             
                                                                                                                             
                                                                                                                             
　
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