曝光台 注意防骗
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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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动力机械和机身手册1(69)
