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CESSNA
SECTION
5
MODEL
182S
PERFORMANCE
Total distance
to
clear
a
SO-foot
obstacle, zero
wind
2035
Decrease
in
total distance
(2035
feet
x
13%)
-ry
Corrected total distance
to clear
SO-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
prof
ile
charÌ
presented in
Figure
5-10,
and
the endurance profile chaft
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
chaft,
Figure
5-9, is
entered
at
8000 feet
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
21
inches
of manifold pressure, which results
in
the following:
Power
True airspeed
Cruise
fuelflow
66%
134 Knots
11.3
GPH
Nov
15/00
c-c
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