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Enroute Rate of Climb Vs Density Altitude ...................................... 19
Time, Fuel and Distance to Climb.................................................... 20
Cruise Performance ......................................................................... 21
Cruise Performance (Continued) ..................................................... 22
Cruise Performance (Continued) ..................................................... 23
Range / Endurance Profile ............................................................... 24
Balked Landing Climb Gradient ....................................................... 26
Balked Landing Rate of Climb ......................................................... 27
Landing Distance ............................................................................. 28
Landing Distance ............................................................................. 29
March 2010
5-2 Information Manual
Section 5 Cirrus Design
Performance Data SR22
March 2010
Intentionally Left Blank
Cirrus Design Section 5
SR22 Performance Data
Information Manual 5-3
Introduction
Performance data in this section are presented for operational
planning so that you will know what performance to expect from the
airplane under various ambient and field conditions. Performance data
are presented for takeoff, climb, and cruise (including range &
endurance).
Associated Conditions Affecting Performance
Computed performance data in this section are based upon data
derived from actual flight testing with the airplane and engine in good
condition and using average piloting techniques. Unless specifically
noted in the “Conditions” notes presented with each table, ambient
conditions are for a standard day (refer to Section 1). Flap position as
well as power setting technique is similarly noted with each table.
The charts in this section provide data for ambient temperatures from
-4°F (–20°C) to 104°F (40°C). If ambient temperature is below the
chart value, use the lowest temperature shown to compute
performance. This will result in more conservative performance
calculations. If ambient temperature is above the chart value, use
extreme caution as performance degrades rapidly at higher
temperatures.
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.
March 2010
5-4 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Airspeed Calibration - Normal Static Source
• Note •
Indicated airspeed values assume zero instrument error.
Conditions:
• Power for level flight or maximum continuous, whichever is less.
KIAS
KCAS
Flaps
0%
Flaps
50%
Flaps
100%
60 57 56 57
70 68 68 70
80 79 80 80
90 89 91 89
100 100 101 99
110 111 111 111
120 121 121
130 132
140 142
150 152
160 163
170 173
180 183
190 193
200 204
March 2010
Cirrus Design Section 5
SR22 Performance Data
Information Manual 5-5
Airspeed Calibration - Alternate Static Source
• Note •
Indicated airspeed values assume zero instrument error.
Conditions:
• Power for level flight or maximum continuous, whichever is less.
• Heater, Defroster & Vents .................................................................................. ON
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
March 2010
5-6 Information Manual
Section 5 Cirrus Design
Performance Data SR22
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.
• 3400 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
　
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