Appendix B
Beaver model parameters
This appendix provides the values of several Beaver model parameters, as well as
some general data for this aircraft. A description of the mathematical model itself
can be found in chapter 3. Appendix C will explain the format that was used to
implement these parameters in the MATLAB/SIMULINK environment.
B.1 General aircraft data
From the late 1950’s until the end of 1993, the Faculty of Aerospace Engineering
of Delft University of Technology has operated a De Havilland DHC-2 Beaver aircraft,
specially equipped as ‘flying laboratory’ for flight research experiments. The
Beaver is a high-winged, seven-seat, all metal aircraft. It is powered by a single
Pratt & Whitney radial piston engine of 450 horsepower, which drives a two-bladed
constant-speed propeller. A picture of the aircraft has been shown in figure B.1; some
basic technical data has been presented in table B.1.
The aircraft has a fixed undercarriage. Under normal circumstances, the flapsettings
‘up’ (0), ‘climb’ (15), and ‘take-off’ (35) are used in flight. Other possible
flapsettings are ‘landing’ (50) and ‘full’ (58), but those are rarely applied in practice,
due to the short take-off and landing (STOL) flight characteristics of the Beaver.
The flight model data from ref.[34] were based on measurements in actual flights,
which were made during the 1977-1978 period. Table B.2 lists some typical flight
conditions for the Beaver.
B.2 Flight envelope
Figure B.2 shows the flight envelope of the Beaver, including the manoeuvre points
that were used for the flight-test measurements from ref.[34]. The flight envelope
was obtained from ref.[6]. Notice that the reported maximum altitude of 10000 feet
is not in agreement with the value from table B.1, which was obtained from ref.[29];
most likely the 10000 feet ceiling is an operational restriction caused by the lack of
a built-in oxygen supply system that would be necessary for prolonged operation
above 10000 feet. In addition, the reported ‘never-exceed speed’ Vne according to
figure B.2 is higher than the maximum speed from table B.1; the latter value probably
representing the maximum operational speed Vmo.
300 Appendix B. Beaver model parameters
B.3 Aerodynamic and engine model parameters
Section 3.3 presented models of the nonlinear aerodynamic and propulsive forces for
the Beaver, see equations (3.3) and (3.7). These models are valid over a wide range
of flight conditions, roughly covered by the flight envelope boundaries of figure B.2.
The corresponding model parameters have been listed in tables B.3 and B.4, respectively.
See ref.[34] for more details on how these parameters were obtained.
Manufacturer De Havilland Aircraft of Canada Ltd.
Serial no. 1244
Type of aircraft Single engine, high-wing, seven seat, all-metal aircraft
Wing span b 14.63 m
Wing area S 23.23 m2
Mean aerodynamic chord c 1.5875 m
Wing sweep 0
Wing dihedral 1
Wing profile NACA 64 A 416
Fuselage length 9.22 m
Height 2.74 m
Max. take-off weight 22800 N
Empty weight 14970 N
Engine Pratt and WhitneyWasp Jr. R-985
Max. power 450 Hp at n = 2300 RPM, pz = 26"Hg
Propeller Hamilton Standard, two-bladed metal regulator propeller
Diameter of the propeller 2.59 m
Total contents of fuel tanks 521 l
Contents fuselage front tank 131 l
Contents fuselage center tank 131 l
Contents fuselage rear tank 95 l
Contents wing tanks 2 x 82 l
Most forward admissible c.g. position 17.36% c at 16989 N; 29.92% c at 22800 N
Most backward admissible c.g. position 40.24% c
Maximum speed 71.4 m/sec ?
Cruising speed 58 m/sec ?
Initial climb gradient 1020 f t/NM = 17% ?
Ceiling 5486 m
Table B.1: General aircraft data of the DHC-2 Beaver, PH-VTH. These data were obtained
from refs.[34] and [29]; the latter figures have been marked by a star symbol: ?.
Figure B.1: The De Havilland DHC-2 Beaver aircraft
B.3. Aerodynamic and engine model parameters 301
10 20 30 40 50 60 70 80 90
0
2000
4000
6000
8000
10000
12000
V [ m/s ]
H [ ft ]
5510
3506 4506 5506
3004
3502 4502 5502 6002
mfliagnhot eeunvvreel oppoein t
Vs = 26.75 Vn e = 80.25 Figure B.2: The flight envelope of the De Havilland DHC-2 Beaver aircraft
Flight condition df [deg] n [RPM] pz ["Hg] V [kts] ˙H [ft/min]
Take-off 35 2350 36.5 70 800/900
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