DA20-100 ‘Katana’ 4X Manual
PERFORMANCE
Neither the software nor the documentation may
be used for real aviation and training purposes.
05<04
page
5.3.2 CRUISING PERFORMANCE
Fuel flow is given in US-gal.
Data labelled * give a basis for interpolation. These values may not be attained at the
stated altitude. To maintain constant performance at non standard temperature
gradient:
Raise manifold pressure by 0.7 in.Hg at ISA + 18° F (10° C)
Lower manifold pressure by 0.7 in.Hg at ISA - 18° F (10° C)
Pressure
altitude
Standard
Temp.
Engine Power in % of maximum continuous power
55%
65%
Ft.
M
°C
°F
RPM
X100
MP
In.Hg
Fuel Flow
L/hr
Gal/hr
RPM
X100
MP
In.Hg
Fuel Flow
L/hr
Gal/hr
0
2000
4000
6000
8000
10000
12000
0
600
1200
1800
2400
3000
3600
13000
4000
15
11
7
3
-1
-5
-8
-11
59
52
45
38
31
24
17
12
19
19
19
20
21
22
22.6
22.6
24.7
24.0
23.3
22.0
21.0
19.7
18.0*
17.0*
13.6
14.4
15.6
16.8
18.0
19.2
20.4*
21.5*
3.6
3.8
4.1
4.4
4.8
5.1
5.4*
5.7*
20
20
21
22
22
22.6
25.7
24.7
23.3
22.7
21.7
20.3*
15.6
16.0
16.8
19.6
21.2
22.4*
4.1
4.2
4.4
5.2
5.6
5.9*
Pressure
altitude
Standard
Temp.
75%
85%
Ft.
M
°C
°F
RPM
X100
MP
In.Hg
Fuel Flow
L/hr
Gal/hr
RPM
X100
MP
In.Hg
Fuel Flow
L/hr
Gal/hr
0
2000
4000
6000
8000
0
600
1200
1800
2400
15
11
7
3
-1
59
52
45
38
31
21
22
22.6
22.6
22.6
27.0
25.7
24.3
23.3
22.0*
18.0
18.4
19.6
23.2
23.6*
4.8
4.9
5.2
6.1
6.2*
22.6
22.6
22.6
27.7
26.7
25.7*
22.0
22.4
25.2*
5.8
5.9
6.7*
Pressure
altitude
Standard
Temp.
Maximum Continous
Power
Maximum Take-Off
Power
Ft.
M
°C
°F
RPM
X100
MP
In.Hg
Fuel Flow
L/hr
Gal/hr
RPM
X100
MP
In.Hg
Fuel Flow
L/hr
Gal/hr
0
2000
4000
6000
0
600
1200
1800
15
11
7
3
59
52
45
38
22.6
22.6
22.6
28.3
27.7*
25.7*
26.0
26.8*
25.2*
6.9
7.1*
6.7*
23.8
29.7*
30.0
7.9*
NOTE:
!
To keep engine wear to a minimum, engine operation below 1900
RPM is not recommended.
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