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Landing
A procedure similar to takeoff should be used for estimating the
landing distance at the destination airport. Figure 5-19 presents
landing distance information for the short field technique. The
distances corresponding to 2000 feet and 20° C are as follows:
• Ground roll .................................................................1248 Feet
• Total distance to land over a 50 foot obstacle ...........2476 Feet
A correction for the effect of wind may be made based on the
headwind and tailwind corrections presented with the landing chart
using the same procedure as outlined for takeoff. Corrections for
runway slope and dry grass may also be applied in like manner.
Demonstrated Operating Temperature
Satisfactory engine cooling has been demonstrated for this airplane
with an outside air temperature 23° C above standard. The value given
is not considered an operating limitation. Reference should be made
to Section 2 for engine operating limitations.
June 2007
5-10 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Figure 5-1
Airspeed Calibration
Normal Static Source
• Note •
• Indicated airspeed values assume zero instrument error.
• KIAS = Knots Indicated Airspeed
• KCAS = Knots Calibrated Airspeed
Conditions: Example:
• Power for level flight or maximum
continuous, whichever is less.
Flaps ........................................... 50%
Indicated Airspeed ............... 85 Knots
Calibrated Airspeed ............. 85 Knots
KIAS
KCAS
Flaps
0%
Flaps
50%
Flaps
100%
60 58
70 68 69
80 79 80 80
90 90 91 90
100 100 101 100
110 110 111
120 121 121
130 131
140 142
150 152
160 162
170 172
180 183
190 193
200 203
June 2007
Information Manual 5-11
Cirrus Design Section 5
SR22 Performance Data
Airspeed Calibration
Alternate Static Source
• Note •
• Indicated airspeed values assume zero instrument error.
• KIAS = Knots Indicated Airspeed
• KCAS = Knots Calibrated Airspeed
Conditions: Example:
• Power for level flight or maximum
continuous, whichever is less.
Flaps............................................50%
Indicated Airspeed................85 Knots
• Heater, Defroster & Vents .............ON
Calibrated Airspeed..............86 Knots
KIAS
KCAS
Flaps
0%
Flaps
50%
Flaps
100%
60 62
70 71 73
80 80 81 82
90 90 91 92
100 100 101 101
110 110 111
120 120 121
130 130
140 140
150 150
160 160
170 170
180 180
190 190
200 199
Figure 5-2
June 2007
5-12 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Figure 5-3
Altitude Correction
Normal Static Source
• Note •
• Indicated airspeed values assume zero instrument error.
• KIAS = Knots Indicated Airspeed
• KCAS = Knots Calibrated Airspeed
Conditions: Example:
• Power for level flight or maximum
continuous, whichever is less.
Flaps ............................................. 0%
Indicated Airspeed ............. 120 Knots
Desired Altitude..................12,000 FT
Altitude Correction ...................-13 FT
Altitude to Fly .....................11,987 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 8 6 3 0 -9 -19 -31 -44 -56
5000 10 7 4 0 -10 -23 -36 -51 -65
10000 11 8 5 0 -12 -26 -42 -59 -76
15000 13 10 5 0 -14 -31 -50 -70 -90
50%
S.L 14 3 -6 -12 -6
5000 17 4 -7 -14 -7
10000 19 4 -9 -17 -8
100%
S.L 13 8 3 0 -1
5000 15 9 3 0 -1
10000 17 10 4 0 -2
June 2007
Information Manual 5-13
Cirrus Design Section 5
SR22 Performance Data
Altitude Correction
Alternate Static Source
• Note •
• Indicated airspeed values assume zero instrument error.
• KIAS = Knots Indicated Airspeed
• KCAS = Knots Calibrated Airspeed
Conditions: Example:
• Power for level flight or maximum
continuous, whichever is less.
Flaps..............................................0%
Indicated Airspeed..............120 Knots
• Heater, Defroster, & Vents.............ON Desired Altitude ................. 12,000 FT
Altitude Correction..................... -4 FT
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(38)
