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WI = 51,211.256N
Then, the corresponding fuelload is given by
Wf = Wo - Wl
= 29,132.644 N
-@
V 3k
-[l~-
V3~0 6
F[
::.}
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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