P/N 11934-003
5-7
Cirrus Design
Section 5
SR20
Performance Data
The fuel estimate for climb is:
• Fuel to climb (standard temperature) ............................ 2.1 Gal.
• Increase due to non-standard temp. (2.1 x 0.13) .......... 0.3 Gal.
• Corrected fuel to climb (2.1 + 0.3) ................................. 2.4 Gal.
Procedure for the distance to climb is:
• Distance to climb (standard temperature) .................... 15.0 NM
• Increase due to non-standard temp. (9.0 x 0.13) .......... 2.0 NM
• Corrected distance to climb (9.0 + 1.2) ........................ 17.0 NM
Cruise
The selected cruise altitude should be based upon airplane
performance, trip length, and winds aloft. A typical cruise altitude and
the expected winds aloft are given for this sample problem. Power
selection for cruise should be based upon the cruise performance
characteristics tabulated in Figure 5-15, and the range/endurance
profile presented in Figure 5-16.
The relationship between power and range as well as endurance is
shown in the range/endurance profile chart, Figure 5-16. Note that fuel
economy and range are substantially improved at lower power
settings.
The cruise performance chart, Figure 5-15, is entered at 6000 feet
altitude and 30
°
C above standard temperature. These values are
conservative for the planned altitude and expected temperature
conditions. The engine speed chosen is 2500 RPM at approximately
55% power, which results in the following:
• Power (MAP = 19.4) ............................................................ 53%
• True airspeed ............................................................. 131 Knots
• Cruise fuel flow............................................................. 9.2 GPH
Reissue A
Содержание SR20
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