Cessna 152 - Cruise Performance and Fuel Data

CESSNA
MODEL
152
CRUISE
SECTION
5
PERFORMANCE
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
deter-
mined
based
on
several
considerations.
These
include
the
cruise
perfor-
mance
characteristics
presented
in
figure
5-7,
the
range
profile
chart
presented
in
figure
5-8,
and
the
endurance
profile
chart
presented
in
figure
5-9.
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.
The
range
profile
chart
indicates
that
use
of
65%
power
at
5500
feet
yields
a
predicted
range
of
375
nautical
miles
under
no
wind
conditions.
The
endurance
profile
chart,
figure
5-9,
shows
a
corresponding
3.9
hours.
The
range
figure
of
375
nautical
miles
is
corrected
to
account
for
the
expected
10
knot
headwind
at
5500 feet.
Range,
zero
wind
Decrease
in
range
due
to
wind
(3.9
hours
" 10
knot
headwind)
Corrected
range
375
39
336Nautical
Miles
This
indicates
that
the
trip
can
be
made
without
a
fuel
stop
using
approximately
65%
power.
The
cruise
performance
chart,
figure
5-7,
is
entered
at
6000
feet
altitude
and
20°C
above
standard
temperature.
These
values
most
nearly
corres-
pond
to
the
planned
altitude
and
expected
temperature
conditions.
The
engine
speed
chosen
is
2400
RPM,
which
results
in
the
following:
Power
True
airspeed
Cruise
fuel
flow
64%
99
Knots
5.2GPH
The
power
computer
may
be
used
to
determine
power
and
fuel
consump-
tion
more
accurately
during
the
flight.
FUEL
REQUIRED
The
total
fuel
requirement
for
the
flight
may
be
estimated
using
the
performance
information
in
figures
5-6
and
5-7.
For
this
sample
problem,
figure
5-6
shows
that
a
climb
from
2000
feet
to
6000
feet
requires
1
gallon
of
1
July
1978
5-5