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                                     WI = 51,211.256N
 Then, the corresponding fuelload is given by
                                   Wf = Wo - Wl
                                                                        = 29,132.644 N
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V 3k
-[l~-
V3~0 6
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120             PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
                                              Example 2.8
     A propeller aircraft weighs 50,000 N and has a wing area of 30 m2.1ts recipro-
 cating engine produces a thrust of 840 kW, and the propulsive efficiencyis 0.85. The
drag polar of the aircraft is given by CD  = 0.025+0.05C~ and CL:nux =  1.60*
The specific fuel consumption is.3.0 N per kW/h. For a fuel load of 10,000 N,
determine the best range and be,st endurance if the aircraft fiies at an altitude of
3000 m (a = 0.7423).
                       R=(7 )E V-(V~)
For maximum range, we have
                           E -Em .
                                                        I
    =T
                                                   1
             ~---- -
                                                                                              ! * 0.025a -0 05
                                             - 14.1421
CL
The specific fuel consumption c is given in N/kWfh. We have to convertit in terms
of N per Nm/s. We have 1 kW - 1000 Nm/s. With this,
        3.ON
                            c= _-           . .
                         lOOONns36 Os '
The range is given by
3.0
1000 * 3600 m
R= (7 )E V-(~W,)
AIRCRAFT PERFORMANCE
121
Substituting,
      R- '3600*1000*0.
                                                                     O 85)14.1421  e.(~: o~)
　
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