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                ~
                                                                    -  12.8172 km
               -      .
                                            Ah = hf - h,
                                                                                    = 2.8172 km
                   -.
Approximate climb angle, tany = 2.8172]2400 - 0.0012 rad = 0.0673 deg.
rfhus, we observe that y is verjr small as assumed.
     The maximum constant-altitude range is given by Eq. (2.148),
                   Rmax = (:,) ( /:. )-
For (f~-] CDXmx, we have
CL -
[,~ - ,~]
           - 0.3333
CD = 0.02+ 0.06*0.33332
     - 0.0266
so that
Substituting,
AIRCRAFT PERFORMANCE
 J:.) ax = ~/:.
               - 21.705
2400*103 = (2~33600) (21.705)
119
[,~- ~]
Solving, W1=50,697.024 N, and Wf = Wo - Wi - 29,646.87 N. Thus, t:he
fuel consumption for constant-altitude range is slightly smaller compared to the
constant-velocitY (Breguet) range. However, the disadvantage is that the flighf
velocit3r continuously varies during the cruise.
     The decreasein the range because ofheadwind for the constant-altit,ude program
is given by Eq. (2.165),
               AR =-E (1  Vw Lv WO
                Wl
                0,333                ;43.9
                           = -O 0~11 (3(.~0) .10.0. h,~:;7.5
                                        -. -162.9982 km
Similarly, the decrease in range for constant-velocity (Breguet) case is given by
                    AR--Em i,)vw e.~v,
Substituting, we get
                                               AR - -187.7525 km
The maximum endurance is given by
                                tmax = (1)Em e.v~
Substituting,
                                                            3600 *14.433 *  av 80,343.9
       5*3600--*    , W~
                1.3
　
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