268            PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
      Consider a strip RT of width dyi on the right wing. Let yh denote the spanwise
coordinate along the quarter chordline and c(yh) denote Lhe local chord normal to
the wing leading edge. The component of force along Ox (the stability axis) for
the righ~wing strip RT is given by
dF = -dL sin(cys - ai) - dD cos(as - ai)                 (3.286)
- ~dL(as - ui) - dD
(3.287)
Substituting for as - aL from Eq. (3.283) we have
                   dF : -dLa sec Ap tan A - dD                                          (3.288)
   =-;:p, ,s2A(i+ptanA)2[cI.Ra,secAtjtanA
     ~ p\/o2COS2
                  +CDO,+CDa., (  +~AA)],(yh)dyh          (3.289)
With
                                                                                          aoa' sec A
                                                Ct.R = ~+ p an A                                  (3.290)
where ao = ao(Y) is the sectionallift-curve slope, we have
           dF = _;2 p Vo2,OS2 A(l+ p tan A)
                           x [aoa2 sec2 Ap tan A + CDO.I(1 + B tan A) + CDa.la sec A]
                           x c(yh) dyh                                                                                            (3.291)
The yawing moment caused by the right wing is given by
      NR = -ydF  .                                                  (3.292)
                        =  g p Vo?- COS2 A(l + p tan A)
                           x [aoa,2 sec2 Ap tan A + CDO.I(1 + p tan A) + CDar.la sec A]
            X [,- (yh)yhdy,r                                  (3.293)
 Similarly, the yawing moment caused by the left wing is given by
            N, = gp Vo2.OS2 A(l - p tan A)
                       . X [aoa2 sec2 Ap tan A - CDO.I(1 - p tan A) - CDa.La sec A]
　
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