塞斯纳172飞行员操作手册 Cessna 172 PILOT'S OPERATING HANDBOOK(44)_通航信息_通航_通用航空

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5-9.
The relationship between power and range is illustrated by the range profile chart. Considerable fuel savings and longer range result when lower power settings are used.
The range profile chart indicates that use of 65% power at 5500 feet yields a predicted range of 523 nautical miles with no wind. The endurance profile chart, figure 5-9, shows a corresponding 4.7 hours.
The range figure of 523 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet.
Range, zero wind 523
Decrease in range due to wind
(4.7 hours x 10 knot headwind) 47
Corrected range 476 Nautical Miles
This indicates that the trip can be made without a fuel stop using approximately 65% power.
The cruise performance chart, figure 5-7, is entered at 6000 feet altitude and 20°C above standard temperature. These values most nearly corres¬pond to the planned altitude and expected temperature conditions. The engine speed chosen is 2500 RPM, which results in the following:

Ground roll, zero wind 1075
Decrease in ground roll
(1075 feet x 13%) 140
Corrected ground roll 935 Feet Power
True airspeed Cruise fuel flow 64%
114 Knots 7.1 GPH

Total distance to clear a
50-foot obstacle, zero wind Decrease in total distance
(1915 feet x 13%) Corrected total distance
to clear 50-foot obstacle 1915
249
1666 Feet The power computer may be used to determine power and fuel consump¬tion more accurately during the flight.
FUEL REQUIRED
The total fuel requirement for the flight may be estimated using the performance information in figures 5-6 and 5-7. For this sample problem, figure 5-6 shows that a climb from 2000 feet to 6000 feet requires 1.3 gallons

SECTION 5 CESSNA CESSNA SECTION 5
PERFORMANCE MODEL 172N MODEL 172N PERFORMANCE
of fuel. The corresponding distance during the climb is 9 nautical miles. These values are for a standard temperature and are sufficiently accurate for most flight planning purposes. However, a further correction for the effect of temperature may be made as noted on the climb chart. The approximate effect of a non-standard temperature is to increase the time, fuel, and distance by 10% for each 10°C above standard temperature, due to the lower rate of climb. In this case, assuming a temperature 16°C above standard, the correction would be:
　
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塞斯纳172飞行员操作手册 Cessna 172 PILOT'S OPERATING HANDBOOK(44)