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10000 16 12 6 0 -15 -32 -49 -66 -80
15000 18 14 7 0 -17 -37 -58 -77 -94
50%
S.L 9 2 -4 -10 -16
5000 11 3 -5 -12 -18
10000 12 3 -6 -14 -22
100%
S.L 10 1 -1 2 6
5000 10 -1 1 6 6
10000 37 45 48 50 56
March 2010
Cirrus Design Section 5
SR22 Performance Data
Information Manual 5-7
Altitude Correction - Alternate Static Source
• Note •
Add correction to desired altitude to obtain indicated altitude to fly.
Indicated airspeed values assume zero instrument error.
KIAS: Knots Indicated Airspeed.
Conditions:
• Power for level flight or maximum continuous, whichever is less.
• Heater, Defroster, & Vents.................................................................................. ON
Flaps Press
Alt
CORRECTION TO BE ADDED - FEET
Normal Static Source - KIAS
60 70 80 90 100 120 140 160 180 200
0%
S.L 12 28 43 57 82 104 126 148 172
5000 16 35 54 71 104 136 168 203 242
10000 20 43 66 87 128 169 211 258 311
15000 23 51 78 103 152 200 251 308 373
50%
S.L 43 65 87 108 148
5000 21 32 39 42 26
10000 36 54 70 82 88
100%
S.L 42 56 67 80 95
5000 37 45 48 50 56
10000 61 81 99 119 148
March 2010
5-8 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Temperature Conversion
To convert from Celsius (°C) to Fahrenheit (°F), find, in the shaded columns,
the number representing the temperature value (°C) to be converted. The
equivalent Fahrenheit temperature is read to the right.
 EXAMPLE: 38°C = 100°F.
To convert from Fahrenheit (°F) to Celsius (°C), find in the shaded columns
area, the number representing the temperature value (°F) to be converted.
The equivalent Celsius temperature is read to the left.
 EXAMPLE: 38°F = 3°C.
Temp to Convert
°C or °F
Temp to Convert
°C or °F
Temp to Convert
°C or °F
°C  °F °C  °F °C  °F
-50 -58 -72 -17 2 36 17 62 144
-49 -56 -69 -16 4 39 18 64 147
-48 -54 -65 -14 6 43 19 66 151
-47 -52 -62 -13 8 46 20 68 154
-46 -50 -58 -12 10 50 21 70 158
-44 -48 -54 -11 12 54 22 72 162
-43 -46 -51 -10 14 57 23 74 165
-42 -44 -47 -9 16 61 24 76 169
-41 -42 -44 -8 18 64 26 78 172
-40 -40 -40 -7 20 68 27 80 176
-39 -38 -36 -6 22 72 28 82 180
-38 -36 -33 -4 24 75 29 84 183
-37 -34 -29 -3 26 79 30 86 187
-36 -32 -26 -2 28 82 31 88 190
-34 -30 -22 -1 30 86 32 90 194
-33 -28 -18 0 32 90 33 92 198
-32 -26 -15 1 34 93 34 94 201
-31 -24 -11 2 36 97 36 96 205
-30 -22 -8 3 38 100 37 98 208
-29 -20 -4 4 40 104 38 100 212
-28 -18 0 6 42 108 39 102 216
-27 -16 3 7 44 111 40 104 219
-26 -14 7 8 46 115 41 106 223
-24 -12 10 9 48 118 42 108 226
-23 -10 14 10 50 122 43 110 230
-22 -8 18 11 52 126 44 112 234
-21 -6 21 12 54 129 46 114 237
-20 -4 25 13 56 133 47 116 241
-19 -2 28 14 58 136 48 118 244
-18 0 32 16 60 140 49 120 248
March 2010
Cirrus Design Section 5
SR22 Performance Data
Information Manual 5-9
Outside Air Temperature for ISA Condition
Press
Alt
Feet
ISA-40°C ISA-20°C ISA ISA+10°C ISA+20°C
°C °F °C °F °C °F °C °F °C °F
SL -25 -13 -5 23 15 59 25 77 35 95
1000 -27 -18 -7 18 13 54 23 72 33 90
2000 -29 -20 -9 16 11 52 21 70 31 88
3000 -31 -24 -11 12 9 48 19 66 29 84
4000 -33 -27 -13 9 7 45 17 63 27 81
5000 -35 -31 -15 5 5 41 15 59 25 77
6000 -37 -34 -17 2 3 38 13 56 23 74
7000 -39 -38 -19 -2 1 34 11 52 21 70
8000 -41 -42 -21 -6 -1 30 10 48 20 66
9000 -43 -45 -23 -9 -3 27 7 45 17 63
10000 -45 -49 -25 -13 -5 23 5 41 15 59
11000 -47 -52 -27 -16 -7 20 3 38 13 56
12000 -49 -56 -29 -20 -9 16 1 34 11 52
13000 -51 -59 -31 -23 -11 13 -1 31 9 49
14000 -53 -63 -33 -27 -13 9 -3 27 7 45
15000 -55 -67 -35 -31 -15 6 -5 23 5 41
16000 -57 -71 -37 -34 -17 2 -7 20 3 38
17000 -59 -75 -39 -38 -19 -2 -9 16 1 34
17500 -60 -76 -40 -40 -20 -3 -10 14 0 32
March 2010
5-10 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Stall Speeds
• Note •
Altitude loss during wings level stall may be 250 feet or more.
KIAS values may not be accurate at stall.
Conditions:
• Weight ........................................................................................................3400 LB
• CG..................................................................................................................Noted
　
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