Performance |
DA 40 NG AFM |
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5.3 PERFORMANCE TABLES AND DIAGRAMS
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5.3.1 AIRSPEED CALIBRATION |
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Airspeed Indicator Calibration |
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% |
Indicated |
Calibrated Airspeed [KCAS] |
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% |
Airspeed [KIAS] |
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at Various Flap Settings |
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% |
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% |
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UP |
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T/O |
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LDG |
% |
65 |
Not applicable |
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64 |
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64 |
% |
70 |
70 |
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69 |
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69 |
% |
75 |
75 |
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74 |
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74 |
% |
80 |
79 |
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79 |
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78 |
% |
85 |
84 |
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84 |
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83 |
% |
90 |
89 |
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89 |
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89 |
% |
95 |
93 |
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94 |
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94 |
% |
100 |
98 |
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99 |
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100 |
% |
105 |
103 |
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104 |
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% |
110 |
108 |
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109 |
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% |
120 |
118 |
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% |
130 |
128 |
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% |
140 |
138 |
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Not applicable |
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% |
150 |
149 |
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% |
160 |
159 |
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% |
170 |
170 |
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Page 5 - 4 |
Rev. 3 |
01-Jul-2014 |
Doc. # 6.01.15-E |
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DA 40 NG AFM |
Performance |
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5.3.2 FUEL FLOW
NOTE
The fuel calculations on the FUEL CALC portion of the G1000
MFD do not use the airplane's fuel quantity indicators. The values shown are numbers which are calculated from the last fuel quantity update done by the pilot and actual fuel flow data. Therefore, the endurance and range data is for information only, and must not be used for flight planning.
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Fuel Flow |
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% |
Power Setting [%] |
Fuel Flow [US gal / h] |
Fuel Flow [Liter / h] |
% |
30 |
2.9 |
11.0 |
% |
35 |
3.3 |
12.5 |
% |
40 |
3.7 |
14.0 |
% |
45 |
4.0 |
15.5 |
% |
50 |
4.4 |
16.5 |
% |
55 |
4.7 |
18.0 |
% |
60 |
5.1 |
19.5 |
% |
65 |
5.6 |
21.5 |
% |
70 |
6.1 |
23.0 |
% |
75 |
6.6 |
25.0 |
% |
80 |
7.1 |
27.0 |
% |
85 |
7.6 |
28.5 |
% |
90 |
8.1 |
30.5 |
% |
92 |
8.3 |
31.5 |
% |
100 |
9.4 |
35.5 |
Doc. # 6.01.15-E |
Rev. 3 |
01-Jul-2014 |
Page 5 - 5 |
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Performance |
DA 40 NG AFM |
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5.3.3 PRESSURE ALTITUDE - DENSITY ALTITUDE
Conversion from pressure altitude to density altitude.
pressure altitude [m]
4000
3500
3000
2500
2000
1500
1000
500
0
-500
[ft] |
14000 |
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[ft] |
altitude |
12000 |
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densityalt. |
pressure |
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10000 |
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14000 |
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s |
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t |
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a |
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8000 |
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n |
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12000 |
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r |
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d |
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a |
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d |
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t |
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e |
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10000 |
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6000 |
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m |
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e |
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p |
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r |
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a |
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8000 |
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t |
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u |
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4000 |
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r |
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e |
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6000 |
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2000 |
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4000 |
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0 |
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2000 |
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-2000 |
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0 |
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-20 |
-10 |
0 |
10 |
20 |
30 |
[°C] |
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-4 |
14 |
32 |
50 |
68 |
86 |
[°F] |
density alt. [m]
4000
3500
3000
2500
2000
1500
1000
500
0
temperature
Example: 1. Set 1,013.25 hPa on altimeter and read pressure altitude (900 ft).
2.Establish ambient temperature (+21 EC).
3.Read off density altitude (1800 ft).
Result: |
From a performance calculation standpoint the airplane is at 1800 ft. |
Page 5 - 6 |
Rev. 3 |
01-Jul-2014 |
Doc. # 6.01.15-E |
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DA 40 NG AFM |
Performance |
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5.3.4 INTERNATIONAL STANDARD ATMOSPHERE
Doc. # 6.01.15-E |
Rev. 3 |
01-Jul-2014 |
Page 5 - 7 |
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