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4. High gross weight or overload
5. High Humidity
· Favorable conditions
6. Low density altitude (low altitude runway, low temperature, high pressure)
7. Downhill runway
8. Headwind
9. Low weight
10. Low Humidity
Takeoff performance data shown in the manufacturers' charts indicates the minimum runway
requirements necessary for successful takeoff. Any factor that adversely affects the takeoff distance must
be taken into account to insure safe operation. Consider that the listed minimum distance is for standard
atmospheric conditions, ideal runway and wind conditions.
TAKEOFF PERFORMANCE
0000' & 59 deg
F
2500' & 50 deg
F
5000' & 41 deg
F
7500' & 32 deg
F
GROSS
WT.
POUNDS
IAS@50'
MPH
HEAD
WIND
GRND
RUN
CLEAR
50'
OBS
GRND
RUN
CLEAR
50'
OBS
GRND
RUN
CLEAR
50'
OBS
GRND
RUN
CLEAR
50'
OBS
2300 68 0 865 1525 1040 1910 1255 2480 1565 3855
2300 68 10 615 1170 750 1485 920 1955 1160 3110
Aircraft Performance
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2300 68 20 405 850 505 1100 630 1480 810 2425
2000 63 0 630 1095 735 1325 905 1625 1120 2155
2000 63 10 435 820 530 1005 645 1250 810 1685
2000 63 20 275 580 340 730 425 910 595 1255
1700 58 0 435 780 520 920 625 1095 765 1370
1700 58 10 290 570 355 680 430 820 535 1040
1700 58 20 175 385 215 470 270 575 345 745
Wind direction and velocity significantly affect takeoff distance. A direct headwind will greatest provide
takeoff assist. A 90° crosswind will give no assistance in takeoff. A tailwind component significantly
increases the takeoff roll.
Gross weight affects takeoff performance.
Increased gross weight:
· Requires a higher takeoff speed in order to achieve sufficient lift.
· Results in reduced acceleration due to greater inertia.
· Increases rolling friction , further reduceing acceleration.
Gusting or strong crosswinds require that the aircraft be held on the ground until definite liftoff can be
achieved. Once liftoff has occured, sufficient speed is needed to prevent settling back onto the runway. If
the landing gear contacts the runway when in a sideways drift, undue stress is placed on the landing gear.
Glide Performance
Glide performance is the distance that the aircraft will glide with an inoperative engine. The best distance
is attained by gilding at an angle of attack that provides the maximum lift/drag ratio (L/Dmax).
In the event that the engine becomes inoperative, it is important to establish the maximum glide airspeed
as quickly as possible. This will permit the maximum radius of emergency landing options. While
gliding toward a suitable landing area, effort should be made to identify the cause of the failure. If time
permits, an engine restart should be attempted as shown in the start-up check list.
Climb Performance
The Pilot Operating Handbook will contain a Climb Performance chart or Table similar to the one below
for a given aircraft. Note that 4 different tables are provided. (Sea Level, 5000 ft, 10,000 ft and 15,000
ft). Note that these altitudes are PRESSURE ALTITUDES and the respective temperatures are Standard
Aircraft Performance
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Temperatures for those altitudes. In other words, the values are given for standard Density Altitudes.
MAXIMUM RATE OF CLIMB DATA
Sea Level & 59° F 5000' & 41° F 10,000' & 23° 15,000 & 5° F
Gross
Weight
lbs.
Ind.
Airspeed
mph
Rate
of
climb
ft/min
Fuel
Used
gal.
Ind.
Airspeed
mph
Rate
of
Climb
ft/min
Fuel
Used
gal
Ind.
Airspeed
Ft/min
Rate
of
Climb
ft/min
Fuel
Used
gal.
Ind.
Airspeed
mph
Rate
of
Climb
ft/min
Fuel
Used
gal
2300 82 645 1.0 81 435 2.6 79 230 4.8 78 22 11.5
2000 79 840 1.0 79 610 2.2 76 380 3.6 75 155 6.3
1700 77 1085 1.0 76 825 1.9 73 570 2.9 72 315 4.4
NOTES:
1. Flaps up, full throttle, mixture leaned above 3000 feet for smooth operation.
2. Fuel Used includes, warm-up and take-off allowance.
3. For hot weather, decrease rate of climb 20 ft/min for each 10°F above standard day for the particular altitude.
Example:
Given: Gross weight 2000 lb: Pressure Alt. 5000 ft: Temperature 61° F.
SOLUTION:
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