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KIAS
KCAS
Flaps
0%
Flaps
50%
Flaps
100%
60 61 58 54
70 68 66 63
80 77 74 72
90 85 83 82
100 94 92 92
110 103 102 101
120 112 112
130 121 122
140 131
150 141
160 150
170 160
180 170
190 179
200 189
210 198
Revision 01: 08-26-09
11934-S37 23 of 56
Cirrus Design Section 9
SR20 Supplements
Altitude Correction
Normal 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.
• 3050 LB
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 9 5 0 -11 -23 -36 -49 -59
5000 13 10 5 0 -13 -27 -42 -56 -69
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
Revision 01: 08-26-09
24 of 56 11934-S37
Section 9 Cirrus Design
Supplements SR20
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
Revision 01: 08-26-09
11934-S37 25 of 56
Cirrus Design Section 9
SR20 Supplements
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 ........................................................................................................ 3050 LB
• C.G................................................................................................................. Noted
• Power ................................................................................................................. Idle
• Bank Angle..................................................................................................... Noted
Weight
LB
Bank
Angle
Deg
STALL SPEEDS
Flaps 0%
Full Up
Flaps 50% Flaps 100%Full
Down
KIAS KCAS KIAS KCAS KIAS KCAS
3050
Most
FWD
C.G.
0 69 67 66 63 61 59
15 70 68 67 65 62 60
30 74 72 70 68 64 63
45 81 80 76 75 70 70
60 95 95 89 90 83 83
3050
Most
AFT
C.G.
0 69 67 63 60 59 56
15 75 68 64 61 60 57
30 77 72 66 64 62 60
45 83 79 72 71 68 67
60 99 94 85 85 79 79
Revision 01: 08-26-09
26 of 56 11934-S37
Section 9 Cirrus Design
Supplements SR20
Wind Components
• Note •
• The maximum demonstrated crosswind is 20 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
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西锐20飞机信息手册CIRRUS DESIGN SR20 AIRPLANE INFORMATION MA(131)
