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-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
Information Manual 5-15
Cirrus Design Section 5
SR20 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
Figure 5-6
March 2010
5-16 Information Manual
Section 5 Cirrus Design
Performance Data SR20
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 .................................. 3000 LB Flaps .....................................Up (0%)
• C.G. ..........................................Noted Bank Angle....................................15°
• Power............................................Idle
• Bank Angle ...............................Noted Stall Speed.......... 66 KIAS | 68 KCAS
Weight
LB
Bank
Angle
Deg
STALL SPEEDS
Flaps 0%Full Up Flaps 50%
Flaps 100%Full
Down
KIAS KCAS KIAS KCAS KIAS KCAS
3000
Most
FWD
C.G.
0 65 67 61 63 56 59
15 66 68 62 64 57 60
30 70 72 65 68 61 63
45 78 80 72 75 67 70
60 92 95 86 89 80 83
3000
Most
AFT
C.G.
0 64 66 59 62 54 57
15 65 67 60 63 55 58
30 69 71 64 66 58 61
45 76 78 71 73 64 68
60 90 93 84 87 76 81
March 2010
Information Manual 5-17
Cirrus Design Section 5
SR20 Performance Data
Wind Components
• Note •
• The maximum demonstrated crosswind is 21 knots. Value not considered limiting.
Conditions: Example:
• Runway Heading...........................10° Wind/Flight Path Angle ................. 50°
• Wind Direction...............................60° Crosswind Component .........12 Knots
• Wind Velocity........................15 Knots Headwind Component..........10 Knots
10°
Tailwind Headwind
0°
ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATH
20°
30°
40°
50°
60°
70°
80°
90°
100°
110°
140° 130° 120°
150°
160°
170°
180°
VELOCITY ~ KNOTS WIND
40
10 20 30 40
WIND COMPONENTS ~ KNOTS
CROSSWIND COMPONENT ~ KNOTS
-20
-10
0
10
20
40
30
SR20_FM05_1014
10
20
30
50
Figure 5-8
March 2010
5-18 Information Manual
Section 5 Cirrus Design
Performance Data SR20
Takeoff Distance
Factors:
The following factors are to be applied to the computed takeoff
distance for the noted condition:
• Headwind - Subtract 10% from computed distance for each 12
knots headwind.
• Tailwind - Add 10% for each 2 knots tailwind up to 10 knots.
• Grass Runway, Dry - Add 20% to ground roll distance.
• Grass Runway, Wet - Add 30% to ground roll distance.
• Sloped Runway - Increase table distances by 22% of the
ground roll distance at Sea Level, 30% of the ground roll
distance at 5000 ft, 43% of the ground roll distance at 10,000 ft
for each 1% of upslope. Decrease table distances by 7% of the
ground roll distance at Sea Level, 10% of the ground roll
distance at 5000 ft, and 14% of the ground roll distance at
　
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