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548  Elementary aeroelasticity

                 The increment of wing lift is  therefore a linear function of  aileron deflection and
                 becomes zero, that is aileron reversal occurs, when

                                                                                   (1 3.17)

                 Hence the aileron reversal speed, Vr, is, from Eq. (13.17)


                                                                                   (13.18)

                   We may define aileron effectiveness at speeds below the reversal speed in terms of
                 the lift ALR produced by an aileron deflection on a rigid wing. Thus
                                       aileron effectiveness = AL/ALR              (13.19)
                 where

                                                                                   (1 3.20)

                 Hence, substituting in Eq. (13.19) for AL from Eq. (13.16) and ALR from Eq. (13.20),
                 we have





                 Equation (13.21) may be expressed in terms of the wing divergence speed  Vd  and
                 aileron reversal speed V, , using Eqs (1 3.3) and (1 3.18) respectively; hence
                                                           1  - V’/V?
                                       aileron effectiveness =                     (13.22)
                                                           1 - V’/Vi
                 We see that when  V, = V,, which occurs when aCL/at = -(acM,o/at)/e, then the
                 aileron is completely effective  at all  speeds. Such a  situation  arises  because the
                 nose-down wing twist caused by aileron deflection is cancelled by the nose-up twist
                 produced by the increase in wing lift.
                   Although the analysis described above is based  on a two-dimensional case it is
                 sometimes  used  in  practice  to  give  approximate  answers  for  finite  wings.  The
                 method is to apply the theory to a representative wing cross-section at an arbitrary
                 spanwise station and use the local wing section properties in the formulae.


                  13.2.2  Aileron effectiveness and reversal (finite wing)


                 We shall again apply strip theory to investigate the aeroelastic effects of aileron deflec-
                 tion on a finite wing. In Fig. 13.6(a) the deflection of the aileron through an angle t
                 produces a rolling velocity p radlsec, having the sense shown. The wing incidence at
                 any section z is thus reduced due to p  by an amount pz/ V. The downward aileron
                 deflection shown here coincides with  an upward deflection on the  opposite wing,
                 thereby contributing to the rolling velocity p. The incidence of the opposite wing is
                 therefore increased by  this direction of  roll. Since we  are concerned with  aileron
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