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Wind Components ........................................................................5-17
Takeoff Distance ...........................................................................5-18
Takeoff Distance ...........................................................................5-19
Takeoff Distance ...........................................................................5-20
Takeoff Climb Gradient .................................................................5-21
Takeoff Rate of Climb ...................................................................5-22
Enroute Climb Gradient ................................................................5-23
Enroute Rate of Climb...................................................................5-24
Enroute Rate of Climb Vs Density Altitude ...................................5-25
Time, Fuel and Distance to Climb.................................................5-26
Cruise Performance ......................................................................5-27
Cruise Performance ......................................................................5-28
June 2007
5-2 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Cruise Performance ......................................................................5-29
Range / Endurance Profile ............................................................5-30
Range / Endurance Profile ............................................................5-31
Range / Endurance Profile ............................................................5-32
Balked Landing Climb Gradient ....................................................5-33
Balked Landing Rate of Climb.......................................................5-34
Landing Distance ..........................................................................5-35
Landing Distance ..........................................................................5-36
June 2007
Information Manual 5-3
Cirrus Design Section 5
SR22 Performance Data
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
–20° C (–4° F) to 40° C (104° F). 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.
All fuel flow data for cruise is based on the recommended lean mixture
setting detailed in Section 4 – Normal Procedures.
June 2007
5-4 Information Manual
Section 5 Cirrus Design
Performance Data SR22
Flight Planning
The performance tables in this section present sufficient information to
predict airplane performance with reasonable accuracy. However,
variations in fuel metering, mixture leaning technique, engine &
propeller condition, air turbulence, and other variables encountered
during a particular flight may account for variations of 10% or more in
range and endurance. Therefore, utilize all available information to
estimate the fuel required for a particular flight. Additionally, verify that
the weather, field length, wind, anticipated turbulence, and other
conditions that affect aircraft performance are judged to be satisfactory
and conducive to safe operations and compliant with the Federal
Aviation Regulations (FARs) or governing regulations, as applicable.
• Note •
Whenever possible, select the most conservative values from
the following charts to provide an extra margin of safety and to
account for events that could occur during a flight.
Sample Problem
The following sample flight problem uses information derived from the
airplane performance charts and tables to determine the predicted
performance for a typical flight.
The first step in flight planning is to determine the aircraft weight and
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(35)
