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Climb 15/0 2000 30.0 70 700/800
Cruise 0 1800 28.0 100 0 (level flight)
Descend 0 1800 15.0 120 -1000
Approach 15 2000 15.0 80 -400/-500
Table B.2: Typical flight conditions for the Beaver (the given values are an average of normally
applied flap deflections, engine settings, and airspeeds); see ref. [34].
302 Appendix B. Beaver model parameters
CX CY CZ
parameter value parameter value parameter value
0 −0.03554 0 −0.002226 0 −0.05504
a 0.002920 b −0.7678 a −5.578
a2 5.459 pb
2V −0.1240 a3 3.442
a3 −5.162 rb
2V 0.3666 qc
V −2.988
qc
V −0.6748 da −0.02956 de −0.3980
dr 0.03412 dr 0.1158 deb2 −15.93
df −0.09447 dra 0.5238 df −1.377
adf 1.106 ˙bb
2V −0.1600 adf −1.261
Cl Cm Cn
parameter value parameter value parameter value
0 0.0005910 0 0.09448 0 −0.003117
b −0.06180 a −0.6028 b 0.006719
pb
2V −0.5045 a2 −2.140 pb
2V −0.1585
rb
2V 0.1695 qc
V −15.56 rb
2V −0.1112
da −0.09917 de −1.921 da −0.003872
dr 0.006934 b2 0.6921 dr −0.08265
daa −0.08269 rb
2V −0.3118 qc
V 0.1595
df 0.4072 b3 0.1373
Table B.3: Coefficients in the aerodynamic model of the Beaver, valid within the 35-55 ms−1
TAS range
CX CY CZ
parameter value parameter value parameter value
dpt 0.1161 − − dpt −0.1563
a · dpt2 0.1453
Cl Cm Cn
parameter value parameter value parameter value
a2 · dpt −0.01406 dpt −0.07895 dpt3 −0.003026
dpt 
Dpt
12
rV2
= C1 + C2
P
12
rV3 with:
(
C1 = 0.08696
C2 = 191.18
Table B.4: Coefficients in the engine forces & moments model of the Beaver, valid within the
35-55 ms−1 TAS range
B.3. Aerodynamic and engine model parameters 303
xc.g. = 0.5996 [m] in FM
yc.g. = 0.0 [m] in FM
zc.g. = -0.8851 [m] in FM
Ixx = 5368.39 [kgm2] in FR
Iyy = 6928.93 [kgm2] in FR
Izz = 11158.75 [kgm2] in FR
Jxy = 0.0 [kgm2] in FR
Jxz = 117.64 [kgm2] in FR
Jyz = 0.0 [kgm2] in FR
m = 2288.231 [kg]
h = 1828.8 [m] (= 6000 [ft])
r = 1.024 [kgm−3]
Table B.5: Aircraft data on which the aerodynamic model of the Beaver is based (FM is the
‘measurement reference frame’, which has been defined in section A.7.1)

Appendix C
Data structure of the FDC model
parameters
This appendix explains the data-format that was used to implement the parameters
of the Beaver dynamics model inMATLAB/SIMULINK. The numerical values of these
parameters has been presented in appendix B; a detailed description of the SIMULINK
model itself can be found in chapter 8.
C.1 Defining the model parameters in the MATLAB workspace
The aircraft model from the FDC toolbox reads its model data from the MATLAB
workspace. The exact structure of this data is highly dependent of the aircraft under
consideration; for the Beaver, most parameters have been stored in three parameter
matrices and one parameter vector. The parameters must be present in the MATLAB
workspace before running a simulation of the airplane model, or applying an
analytical SIMULINK or FDC function to this model.
This data-structure may not be suited for the implementation of different aircraft
models within the FDC structure. Although any suitable data-structure can be used,
it is recommended not to change the definitions of the vector GM1 and matrix GM2,
which contain mass-distribution data and information about the airplane’s geometry,
except for enhancing the model for non-constant mass and/or mass-distribution.
This is due to the fact that these two matrices are used by aircraft-independent subsystems
as well, contrary to the aerodynamic and propulsion parameter matrices AM
and EM, which are used by aircraft-dependent blocks only.
The parameters can be loaded from the file AIRCRAFT.DAT, which can normally
be found in the DATA subdirectory, using the utility DATLOAD (see section 12.4.2). If
this datafile has somehow inadvertently been deleted, it can be re-created by running
the program MODBUILD (see section 12.6.1). The definitions of the parameter vector
and matrices for the Beaver model will be given below; the numerical values of the
parameters have been listed in appendix B, along with some general information
about the Beaver aircraft.
To change the values of the parameters, e.g. in order to implement a model of a
different aircraft, the easier method is to create a customized copy of MODBUILD.M.
　
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