曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

center of gravity, as well as information about the flight. For this
sample problem, the following information is known:
Airplane Configuration:
• Takeoff weight........................................................3400 Pounds
• Usable fuel.................................................................81 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
June 2007
Information Manual 5-5
Cirrus Design Section 5
SR22 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 3400 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 .................................................................1385 Feet
• Total distance to clear a 50 foot obstacle ...................2107 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 ................................................. 1385 feet
• Decrease in ground roll (1385 feet x 0.092) .................. 127 feet
• Corrected ground roll................................................... 1258 feet
• Total distance to clear a 50 foot obstacle, zero wind ... 2107 feet
June 2007
5-6 Information Manual
Section 5 Cirrus Design
Performance Data SR22
• Decrease in total distance (2107 feet x 0.092) ..............194 feet
• Corrected total distance to clear 50 foot obstacle .......1913 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.
Climb
The takeoff and enroute rate-of-climb and climb gradient tables,
Figures 5-10 through 5-13, present maximum rate of climb and climb
gradient for various conditions. The time, fuel, and distance to climb
table, Figure 5-14, allows determination of the time, fuel, and distance
to climb from sea level to a specified pressure altitude. To determine
the values to be used for flight planning, the start-of-climb time, fuel,
and distance values are subtracted from the end-of-climb (cruise
altitude) values. Again, conservative values are obtained by using the
next lower altitude value for start of climb or next higher altitude values
for end of climb. Using conservative values for the sample data, the
following calculations are made:
Start-of-climb values (SL to 1750 feet):
• Time to climb .......................................................... 0.7 minutes
• Distance to climb ............................................................ 1.0 NM
• Fuel to climb ................................................................. .0.3 Gal.
End-of-climb values (SL to 6500 feet):
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(36)