CESSNA
MODEL 182T NAV
Ill
SECTION 5
PERFORMANCE
SAMPLE PROBLEM
(Continued)
Total distance to clear a
50-foot obstacle, zero wind 2035
Decrease in total distance
(2035 feet
X
13%)
-265
-
Corrected total distance
to clear 50-foot obstacle 1770 Feet
CRUISE
The cruising altitude should be selected based on a consideration
of trip length, winds aloft, and the airplane's performance. A typical
cruising altitude and the expected wind
enroute have been given for
this sample problem. However, the power setting selection for
cruise must be determined based on several considerations. These
include the cruise performance characteristics presented in Figure
5-9, the range profile chart presented in Figure 5-10, and the
endurance profile chart presented in Figure 5-1 1.
The relationship between power and range is illustrated by the
range profile chart. Considerable fuel savings and longer range
result when lower power settings are used. For this sample
problem, a cruise power of approximately
60% will be used.
The cruise performance chart, Figure 5-9, is entered at 8000 feet
pressure altitude and 20°C above standard temperature. These
values most nearly correspond to the planned altitude and expected
temperature conditions. The engine speed chosen is 2400 RPM
and 19 inches of manifold pressure, which results in the following:
Power
60%
True airspeed 130 Knots
Cruise fuel flow 10.7 GPH
(Continued Next Page)
U.S. 5-5
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