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• 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
Revision A5
P/N 13772-001 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
2500 25.4 84% 173 20.0 80% 173 19.0 76% 168 19.5
2500 24.4 80% 170 19.0 76% 170 18.0 72% 165 18.8
2500 23.4 76% 167 18.0 72% 167 17.0 68% 162 18.1
4000 Feet Pressure Altitude
ISA - 30° C (-23° C) ISA (7° C) ISA + 30° C (37° C)
RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH
2700 25.4 96% 185 22.9 91% 185 21.6 87% 180 20.8
2600 25.4 92% 182 21.9 87% 182 20.7 83% 177 20.6
2500 25.4 87% 178 20.6 82% 178 19.5 78% 173 19.9
2500 24.4 82% 175 19.5 78% 175 18.5 74% 170 19.2
2500 23.4 78% 172 18.5 74% 172 17.5 70% 167 18.5
2500 22.4 73% 169 17.4 69% 169 16.5 66% 163 17.7
2500 21.4 69% 165 16.4 65% 165 15.5 62% 159 16.9
6000 Feet Pressure Altitude
ISA - 30° C (-27° C) ISA (3° C) ISA + 30° C (33° C)
RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH
2700 23.5 89% 184 21.2 85% 184 20.1 81% 179 19.6
2600 23.5 85% 181 20.3 81% 181 19.2 77% 176 19.1
2500 23.5 80% 177 19.1 76% 177 18.1 72% 172 18.3
2500 22.5 76% 174 18.1 72% 174 17.1 68% 169 17.6
2500 21.5 72% 170 17.0 68% 170 16.1 64% 165 16.9
2500 20.5 67% 166 15.9 64% 166 15.1 60% 161 16.1
2500 19.5 63% 162 14.9 59% 162 14.1 56% 157 15.3
Figure 5-16
Sheet 1 of 3
Revision A7
5-28 P/N 13772-001
Section 5 Cirrus Design
Performance Data SR22
Figure 5-16
Cruise Performance
8000 Feet Pressure Altitude
ISA - 30° C (-31° C) ISA (-1° C) ISA + 30° C (29° C)
RPM MAP PWR KTAS GPH PWR KTAS GPH PWR KTAS GPH
2700 21.7 83% 183 19.7 78% 183 18.6 75% 178 17.7
2600 21.7 79% 180 18.8 75% 180 17.8 71% 175 17.0
2500 21.7 75% 176 17.7 71% 176 16.8 67% 171 16.0
2500 20.7 70% 172 16.7 66% 172 15.8 63% 167 15.0
2500 19.7 66% 168 15.6 62% 168 14.8 59% 163 14.0
2500 18.7 61% 163 14.5 58% 163 13.8 55% 158 13.1
2500 17.7 57% 159 13.5 54% 159 12.8 51% 153 12.1
10,000 Feet Pressure Altitude
　
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