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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 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
10,000 ft for each 1% of downslope.
• Caution •
The above corrections for runway slope are required to be
included herein. These corrections should be used with
caution since published runway slope data is usually the net
slope from one end of the runway to the other. Many runways
will have portions of their length at greater or lesser slopes
than the published slope, lengthening (or shortening) takeoff
ground roll estimated from the table.
• If brakes are not held while applying power, distances apply
from point where full throttle and mixture setting is complete.
• For operation in outside air temperatures colder than this table
provides, use coldest data shown.
• For operation in outside air temperatures warmer than this table
provides, use extreme caution.
Conditions: Example:
• Winds.......................................... Zero Outside Air Temp ....................... 25°C
• Runway................... Dry, Level, Paved Weight...................................3000 LB
• Flaps........................................... 50% Pressure Altitude...................2000 FT
• Power.................................. Maximum Headwind ............................. 12 Knots
set before brake release Runway ............................. Dry, Paved
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 1148-126(39)
