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• Time to climb .......................................................... 6.0 minutes
• Distance to climb .......................................................... 10.5 NM
• Fuel to climb ................................................................. 2.4 Gal.
Climb values (1750 to 6500 feet):
• Time to climb (end 6.0 - start 0.7) ........................... 5.3 minutes
• Distance to climb (end 10.5 - start 1.0) .......................... 9.5 NM
• Fuel to climb (end 2.4 - start 0.3) .................................. 2.1 Gal.
The above values reflect climb for a standard day and are sufficient for
most flight planning. However, further correction for the effect of
temperature on climb can be made. The effect of a temperature on
June 2007
Information Manual 5-7
Cirrus Design Section 5
SR22 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........................ 9.5 NM
• Increase due to non-standard temp (9.5 x 0.13) ........... 1.2 NM
• Corrected distance to climb (9.5 + 1.2) ........................ 10.7 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 for maximum power is 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 = 19.5) ............................................................56%
• True airspeed .............................................................157 Knots
• Cruise fuel flow........................................................... 15.3 GPH
June 2007
5-8 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Fuel Required
The total fuel requirement for the flight may be estimated using the
performance information obtained from Figures 5-14 and 5-15. The
resultant cruise distance is:
• Total distance (from sample problem) ........................ 560.0 NM
• Climb distance (corrected value from climb table)........ 10.7 NM
• Cruise distance (total distance - climb distance) ........ 549.3 NM
Using the predicted true airspeed from the cruise performance table,
Figure 5-15, and applying the expected 10-knot headwind, the ground
speed for cruise is expected to be 147 knots. Therefore, the time
required for the cruise portion of the trip is:
• 549.3 NM/147 knots = 3.7 hours.
The fuel required for cruise is:
• 3.7 hours x 15.3 GPH = 56.6 gallons.
From the 6000 ft Cruise Table (Figure 5-15), a 45 minute IFR reserve
at approximately 55% power requires:
• 45/60 x 15.3 GPH = 11.5 gallons
The total estimated fuel required is as follows:
• Engine start, taxi, and takeoff ................................... 1.5 gallons
• Climb ........................................................................ 2.4 gallons
• Cruise ..................................................................... 56.6 gallons
• Reserve .................................................................. 11.5 gallons
• Total fuel required................................................... 72.0 gallons
Once the flight is underway, ground speed checks will provide a more
accurate basis for estimating the time enroute and the corresponding
fuel required to complete the trip with ample reserve.
June 2007
Information Manual 5-9
Cirrus Design Section 5
SR22 Performance Data
　
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