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12000 94 706 666 623 577 684
14000 93 581 537 490 441 565
16000 92 454 406 355 303 446
2900
SL 101 1761 1748 1726 1698 1732
2000 100 1629 1610 1584 1552 1596
4000 98 1494 1471 1441 1405 1461
6000 97 1359 1331 1296 1257 1326
8000 96 1222 1189 1151 1108 1191
10000 95 1084 1046 1004 958 1056
12000 94 945 902 855 806 921
14000 93 804 757 706 653 787
16000 92 662 610 556 499 653
June 2007
Information Manual 5-25
Cirrus Design Section 5
SR22 Performance Data
Enroute Rate of Climb Vs Density Altitude
Conditions:
• Power .................................................................................................... Full Throttle
• Mixture ......................................... Per Schedule - Section 4, Max Power Fuel Flow
• Flaps ...........................................................................................................0% (UP)
• Airspeed..................................................................................... Best Rate of Climb
1,000
2,000
3,000
4,000
5,000
6,000
7,000
8,000
9,000
10,000
11,000
12,000
13,000
14,000
15,000
16,000
17,000
400
500
600
700
800
900
1000
1100
1200
1300
1400
1500
1600
1700
1800
3400 LB
2900 LB
Rate of Climb ~ Feet Per Minute
Figure 5-14
June 2007
Density Altitude ~ Feet
5-26 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Figure 5-15
Time, Fuel and Distance to Climb
Factors:
• Taxi Fuel - Add 1.5 gallon for start, taxi, and takeoff.
• Temperature - Add 10% to computed values for each 10º C above standard.
• Fuel flow must be set to the placarded limit for all takeoffs and climbs.
• Cruise climbs or short duration climbs are permissible at best power as long as
altitudes and temperatures remain within those specified in the table.
Conditions: Example:
• Power...............................Full Throttle Outside Air Temp ......................... ISA
• Mixture......... Per Schedule, Section 4 Weight...................................3400 LB
• Fuel Density..................... 6.0 LB/GAL Airport Press.........................1000 FT
• Weight .................................. 3400 LB Pressure Altitude.................12000 FT
• Winds.......................................... Zero
• Climb Airspeed .........................Noted Time to Climb.................11.3 Minutes
Fuel to Climb......................5.6 Gallon
Distance to Climb..................20.5 NM
Press
Alt
FT
OAT
(ISA)
°C
Climb
Speed
KIAS
Rate Of
Climb
FPM
TIME, FUEL, DISTANCE ~ From Sea Level
Time
Minutes
Fuel
U.S. Gal
Distance
NM
SL 15 101 1398 0.0 0.0 0.0
1000 13 100 1339 0.7 0.3 1.0
2000 11 100 1279 1.5 0.7 2.5
3000 9 99 1220 2.5 1.0 4.0
4000 7 98 1160 3.0 1.3 5.5
5000 5 97 1101 4.0 1.7 7.0
6000 3 97 1041 5.0 2.0 8.5
7000 1 96 982 6.0 2.4 10.5
8000 -1 96 922 7.0 2.7 12.0
9000 -3 95 863 8.0 3.1 14.5
10000 -5 95 803 9.5 3.5 16.5
11000 -7 94 744 10.5 3.9 19.0
12000 -9 94 684 12.0 4.4 21.5
13000 -11 93 625 13.5 4.8 24.5
14000 -13 93 565 15.0 5.3 28.0
15000 -15 92 506 17.0 5.8 31.5
16000 -17 92 446 19.0 6.4 35.5
17000 -19 91 387 21.5 7.1 40.0
17500 -20 91 357 24.0 7.8 45.5
June 2007
Information Manual 5-27
Cirrus Design Section 5
SR22 Performance Data
Cruise Performance
Conditions: Example:
• Mixture ............................. Best Power Outside Air Temp...................29° C
• Cruise Weight........................2900 LB RPM ..............................2700 RPM
• Winds ..........................................Zero Cruise Press Alt................ 8000 FT
Note: Subtract 10 KTAS if nose wheel pant
and fairing removed. Lower KTAS by 10% if % Power (24.0 MAP) .............. 75%
nose & main wheel pants & fairings removed. True Airspeed ................ 178 Knots
Cruise Pwr above 85% not recommended. Fuel Flow........................17.7 GPH
2000 Feet Pressure Altitude
ISA - 30° C (-19° C) ISA (11° C) ISA + 30° C (41° C)
RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH
2700 27.4 103% 186 24.6 98% 186 23.3 93% 181 22.0
2600 27.4 99% 183 23.5 94% 183 22.2 89% 178 21.5
2500 27.4 93% 179 22.1 88% 179 20.9 84% 174 20.8
2500 26.4 89% 176 21.1 84% 176 19.9 80% 171 20.2
　
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