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conservative for the planned altitude and expected temperature
conditions. The engine speed chosen is 2500 RPM at approximately
55% power, which results in the following:
• Power (MAP = 19.4) ............................................................53%
• True airspeed .............................................................131 Knots
• Cruise fuel flow............................................................. 9.2 GPH
March 2010
5-8 Information Manual
Section 5 Cirrus Design
Performance Data SR20
Fuel Required
The total fuel requirement for the flight may be estimated using the
performance information obtained from Figures 5-15 and 5-16. The
resultant cruise distance is:
• Total distance (from sample problem) ........................ 560.0 NM
• Climb distance (corrected value from climb table)........ 17.0 NM
• Cruise distance (total distance – climb distance) ....... 543.0 NM
Using the predicted true airspeed from the cruise performance table,
Figure 5-16, and applying the expected 10-knot headwind, the ground
speed for cruise is expected to be 121 knots. Therefore, the time
required for the cruise portion of the trip is:
• 543.0 NM/121 knots = 4.5 hours.
The fuel required for cruise is:
• 4.5 hours x 9.2 GPH = 41.4 gallons.
From the 6000 ft Cruise Table (Figure 5-16), a 45 minute IFR reserve
at approximately 70% power requires:
• 45/60 x 11.1 GPH = 8.3 gallons
The total estimated fuel required is as follows:
• Engine start, taxi, and takeoff ................................... 1.0 gallons
• Climb ........................................................................ 2.4 gallons
• Cruise ..................................................................... 41.4 gallons
• Reserve .................................................................... 8.3 gallons
• Total fuel required................................................... 53.1 gallons
Once the flight is underway, ground speed checks will provide a more
accurate basis for estimating the time enroute and the corresponding
fuel required to complete the trip with ample reserve.
March 2010
Information Manual 5-9
Cirrus Design Section 5
SR20 Performance Data
Landing
A procedure similar to takeoff should be used for estimating the
landing distance at the destination airport. Figure 5-20 presents
landing distance information for the short field technique. The
distances corresponding to 2000 feet and 20 C are as follows:
• Ground roll .................................................................1110 Feet
• Total distance to land over a 50-foot obstacle ...........2166 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.
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
5-10 Information Manual
Section 5 Cirrus Design
Performance Data SR20
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
• Weight .................................. 3000 LB
Calibrated Airspeed ............. 86 Knots
KIAS
KCAS
Flaps
0%
Flaps
50%
Flaps
100%
50 49
60 60 60
70 72 71 71
80 81 81 81
90 91 91 91
100 101 101 101
110 111 111
120 120 120
130 130
140 140
150 150
160 160
170 170
180 180
190 190
200 200
March 2010
Information Manual 5-11
Cirrus Design Section 5
SR20 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%
　
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