Specifications

Information Manual 5-7
Cirrus Design Section 5
SR20 Performance Data
climb performance is to increase the time, fuel, and distance to climb
by approximately 10% for each 10 C above ISA. In our example,
using a temperature of ISA + 13 C, the correction to be applied is
13%.
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. (15.0 x 0.13) ........ 1.9 NM
• Corrected distance to climb (15.0 + 1.9) ...................... 16.9 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 5-16, and the range/endurance
profile presented in Figure 5-17.
The relationship between power and range as well as endurance is
shown in the range/endurance profile chart, Figure 5-17. Note that fuel
economy and range are substantially improved at lower power
settings.
The cruise performance chart, Figure 5-16, 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
March 2010