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Altitude to Fly..................... 11,996 FT
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 1 0 -1 -1 -3 -3 -1 4 13
5000 2 0 -1 -2 -3 -3 -1 5 15
10000 2 1 -1 -2 -4 -4 -1 6 18
15000 2 1 -1 -2 -4 -4 -1 7 21
50%
S.L -7 -6 -5 -5 -9
5000 -8 -7 -6 -6 -10
10000 -9 -8 -7 -7 -12
100%
S.L -14 -17 -18 -16 -10
5000 -16 -20 -21 -19 -12
10000 -18 -23 -25 -22 -14
Figure 5-4
June 2007
5-14 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Figure 5-5
Temperature Conversion
• Note •
• 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
June 2007
Information Manual 5-15
Cirrus Design Section 5
SR22 Performance Data
Outside Air Temperature
for
ISA Condition
Example:
Pressure Altitude...................8000 FT
Outside Air Temp....................... 48° F
ISA Condition .................. ISA + 10° C
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
Figure 5-6
June 2007
5-16 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Figure 5-7
Stall Speeds
• Note •
• Altitude loss during wings level stall may be 250 feet or more.
• KIAS values may not be accurate at stall.
Conditions: Example:
• Weight .................................. 3400 LB Flaps .....................................Up (0%)
• C.G. ..........................................Noted Bank Angle....................................15°
• Power............................................Idle C.G........................................ Forward
• Bank Angle ...............................Noted
Stall Speed.......... 71 KIAS | 70 KCAS
Weight
LB
Bank
Angle
Deg
STALL SPEEDS
Flaps 0%Full Up
Flaps 50% Flaps 100%Full
Down
KIAS KCAS KIAS KCAS KIAS KCAS
3400
　
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