Cirrus Design SR22
Section 5 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........................ 9.5 NM • Increase due to non-standard temp (9.5 x 0.13) ........... 1.2 NM • Corrected distance to climb (9.5 + 1.2) ........................ 10.7 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 5-15, and the range/endurance profile for maximum power is presented in Figure 5-16. The relationship between power and range as well as endurance is shown in the range/endurance profile chart, Figure 5-16. Note that fuel economy and range are substantially improved at lower power settings. The cruise performance chart, Figure 5-15, is entered at 6000 feet altitude and 30° C above standard temperature. These values are 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 = 19.5) ............................................................ 56% • True airspeed ............................................................. 157 Knots • Cruise fuel flow........................................................... 15.3 GPH
Information Manual June 2007
5-7
飞行翻译公司 www.aviation.cn 本文链接地址：西瑞22飞机信息手册 AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22_split_3.pdf
Section 5 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........................ 9.5 NM • Increase due to non-standard temp (9.5 x 0.13) ........... 1.2 NM • Corrected distance to climb (9.5 + 1.2) ........................ 10.7 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 5-15, and the range/endurance profile for maximum power is presented in Figure 5-16. The relationship between power and range as well as endurance is shown in the range/endurance profile chart, Figure 5-16. Note that fuel economy and range are substantially improved at lower power settings. The cruise performance chart, Figure 5-15, is entered at 6000 feet altitude and 30° C above standard temperature. These values are 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 = 19.5) ............................................................ 56% • True airspeed ............................................................. 157 Knots • Cruise fuel flow........................................................... 15.3 GPH
Information Manual June 2007
5-7
飞行翻译公司 www.aviation.cn 本文链接地址：西瑞22飞机信息手册 AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22_split_3.pdf
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