PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL1(45)

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Kinematic equations as given by Eqs. (2.9) and (2.10) are
                                                  x - V cos y                                      (2.31)
                                                           h = V sin y                                             (2.32)
Generally, the glide angle y is small so that we have
                                           D+ Wy - 0                                 (2.33)
                                          L - W                                 (2.34)
                                        x - V                                (2.35)
                                     h = Vy                             (2.36)
Lift and drag forces are given by
                                                             L -  21p V 2SCL                                             (2,37)
                               D = ;p V2SCD
                                         = ~2pl/2'      o +kCZ)
           _ r2S(CDO.          (2.38)
The velocity is given by
'v _
(2.39)
AIRCRAFT PERFORMANCE
The glide angle can be obtained from Eqs. (2.33) and (2.34) as
                        D
                                  )/ = -W
                        D
       =-L
　
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