PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL1(70)

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            .    3.0
                                     -. 3,218,840.9 m
                                 - 3218.8409 km
To cover this range, we have two options: 1) cruise at constant altitude or 2) cruise
at constant velocit)r.
     For the constant-altitude cruise; the 11ight velocity varies continuously from  Vo
to Vi as the weight decreases from Wo = 50,000 N to Wi = 50,000 - 10,000 _
40,000 N, where
iVO -
-. 72.0021 m/s
VI :
                                       - 64.4007 m/s
For constant-velocity range, V : Vo, and the airplane gains altitude during the
cruise. The height gained is obtained as follows.
              WI
                   crf = WOUr'
         40,(
                                                       = 5~~ .0.7423
                                    - 0.5938
Then,
                                       hf = 44.3(1 - al.235)
                                                       = 44.3(1 _ 0.59380'235)
                N
                                                       - 5.1066 km
                ~
                                           Ah = hf - hi
                                                                                 - 2.1066 km
122             PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
The maximum endurance is given by
We have
tmax = (-, .) (-,.) _x
 -,.)- = -,
    1
=4
                                           - 13.5540
Substituting, we obtain tmax - 14.9733 h.
2.8 TurningFlight
       In this section we will study the aircraft performance in tunung flight. Whereas
the turning fiight is one of the routine flights for the majority of aircraft,it is a key
tactical maneuver for the combat aircraft.In addition, the turning performance is
one important metric of air superiority of the fighter aircraft.
　
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