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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
center of gravity, as well as information about the flight. For this
sample problem, the following information is known:
Airplane Configuration:
• Takeoff weight........................................................3000 Pounds
• Usable fuel.................................................................56 Gallons
Takeoff Conditions:
• Field pressure altitude ................................................1750 Feet
• Temperature ................................................25 C (ISA + 13 C)
• Wind component along runway ......................11 knot headwind
• Runway Condition ............................................Dry, level, paved
• Field length .................................................................3000 Feet
March 2010
Information Manual 5-5
Cirrus Design Section 5
SR20 Performance Data
Cruise Conditions:
• Total distance ................................................560 Nautical Miles
• Pressure altitude ........................................................6500 Feet
• Temperature ................................................20 C (ISA + 17 C)
• Expected wind enroute..................................10 Knot Headwind
Landing Conditions:
• Field pressure altitude................................................2000 Feet
• Temperature ................................................20 C (ISA + 10 C)
• Field length.................................................................3000 Feet
Takeoff
The takeoff distance tables, Figure 5-9, show the takeoff ground roll
and horizontal distance to reach 50 feet above ground level. The
distances shown are based on the short field technique.
Conservative distances can be established by reading the tables at the
next higher value of weight, altitude and temperature. For example, in
this particular sample problem, the takeoff distance information
presented for a weight of 3000 pounds, takeoff field pressure altitude
of 2000 feet, and a temperature of 30 C should be used. Using the
conservative values results in the following:
• Ground roll .................................................................1940 Feet
• Total distance to clear a 50-foot obstacle ...................2734 Feet
Since the takeoff distance tables are based upon a zero wind
conditions, a correction for the effect of winds must be made. Use the
wind components chart, Figure 5-8 to determine the crosswind and
the headwind (or tailwind) component of the reported winds.
Using the 11-knot headwind component, the following corrections can
be made:
• Correction for headwind (10% for each 12 knots) ..............9.2%
• Ground roll, zero wind ................................................. 1940 feet
• Decrease in ground roll (1940 feet x 0.092) .................. 178 feet
• Corrected ground roll................................................... 1762 feet
• Total distance to clear a 50-foot obstacle, zero wind... 2734 feet
March 2010
5-6 Information Manual
Section 5 Cirrus Design
Performance Data SR20
• Decrease in total distance (2734 feet x 0.092) ..............252 feet
• Corrected total distance to clear 50-foot obstacle .......2482 feet
Corrections for grass runways and sloped runways are also applicable
and should be applied. These corrections are calculated in the same
manner as the wind correction above. Refer to Figure 5-9 for
correction factors to be applied.
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西锐20飞机信息手册 SR22 AIRPLANE INFORMATION MANUAL 1148-126(35)
