曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
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.
Climb
The takeoff and enroute rate-of-climb and climb gradient tables,
Figures 5-10 through 5-14, present maximum rate of climb and climb
gradient for various conditions. The time, fuel, and distance to climb
table, Figure 5-15, 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 .......................................................... 1.3 minutes
• Distance to climb ............................................................ 2.0 NM
• Fuel to climb ................................................................. 0.3 Gal.
End-of-climb values (SL to 6500 feet):
• Time to climb ........................................................ 10.3 minutes
• Distance to climb .......................................................... 17.0 NM
• Fuel to climb ................................................................. 2.4 Gal.
Climb values (1750 to 6500 feet):
• Time to climb (end 10.3 – start 1.3)......................... 9.0 minutes
• Distance to climb (end 17.0 – start 2.0)........................ 15.0 NM
• Fuel to climb (end 2.4 – start 0.3).................................. 2.1 Gal.
The above values reflect climb for a standard day and are sufficient for
most flight planning. However, further correction for the effect of
temperature on climb can be made. The effect of a temperature on
March 2010
Information Manual 5-7
Cirrus Design Section 5
SR20 Performance Data
climb performance is to increase the time, fuel, and distance to climb
by approximately 10% for each 10 C above ISA. In our example,
using a temperature of ISA + 13 C, the correction to be applied is
13%.
The fuel estimate for climb is:
• Fuel to climb (standard temperature) ............................ 2.1 Gal.
• Increase due to non-standard temp. (2.1 x 0.13) .......... 0.3 Gal.
• Corrected fuel to climb (2.1 + 0.3) ................................. 2.4 Gal.
Procedure for the distance to climb is:
• Distance to climb (standard temperature) .................... 15.0 NM
• Increase due to non-standard temp. (15.0 x 0.13) ........ 1.9 NM
• Corrected distance to climb (15.0 + 1.9) ...................... 16.9 NM
Cruise
The selected cruise altitude should be based upon airplane
performance, trip length, and winds aloft. A typical cruise altitude and
the expected winds aloft are given for this sample problem. Power
selection for cruise should be based upon the cruise performance
characteristics tabulated in Figure 5-16, and the range/endurance
profile presented in Figure 5-17.
The relationship between power and range as well as endurance is
shown in the range/endurance profile chart, Figure 5-17. Note that fuel
economy and range are substantially improved at lower power
settings.
The cruise performance chart, Figure 5-16, is entered at 6000 feet
altitude and 30 C above standard temperature. These values are
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
西锐20飞机信息手册CIRRUS DESIGN SR20 AIRPLANE INFORMATION MA(37)
