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moment. Thus, conceptually (Cnr)W < O or wing provides a damping effect in
yaw.
   We have
                           dF -. -dD                                                (4.621)
                                                               1
                                                    = - ;:p(Uo2 _ 2Uory) CDJc(y) dy                          (4.622)
The yawing moment developed by the elemental strip RT is given by
                              dYM = lp(U2 _ 2Uory)CDJc(y)y dy                  (4.623)
The total yawing moment due to the right wing is.given by
                                   Y MR = gp [,' (Uo2 _ 2Uory)CD.lc(y)y dy                  (4.624)
 Similarly, the yawing moment due to the left wing (change y to -y) is given by
                                     1
                                     Y M, = -2 p  [,'  (Uo2 + 2Uor y)CD.Lc(y)y dy                  (4.625)
 so that the total yawing moment is given by
                                            Y M  = -2p Uor [,-' CD.lc(y)y2 dy                          (4.626)
 We have
                                                                        Y M                                            (4.627)
                                                 C" = ~-p U2Sb
Cnr = aa(:c: )                        (4.628)
EQUATIONS OF MOTION AND ESTIMATION OF STABILITY DERIVATIVES 417
   For an untwisted rectangular wing of constant chord and an identical airfoil
section along the span, Eq. (4.629) reduces to
(Cnr)W = -/3 CD,l                                     (4.630)
　
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