!***************************************
!Sample AVL input dataset
!***************************************
Plane Vanilla
!Mach
 0.0    
!IYsym   IZsym   Zsym
 0       0       0.0
!Sref    Cref    Bref
12.0     1.0     15.0
!Xref    Yref    Zref
0.0      0.0      0.0

#--------------------------------------------------
SURFACE 
WING 
!Nchordwise  Cspace  Nspanwise  Sspace
1            1.0     16         -2.0
YDUPLICATE 
0.0
ANGLE
4.0

SECTION
!Xle    Yle    Zle     Chord   Ainc  Nspanwise  Sspace
-0.25   0.     0.      1.000   0.    8          1.0
CONTROL
aileron  1.0  0.0  0. 0. 0.  -1

SECTION
!Xle    Yle    Zle     Chord   Ainc  Nspanwise  Sspace
-0.175  7.5    0.5     0.700   0.    0          0
CONTROL
aileron  1.0  0.0  0. 0. 0.  -1

#--------------------------------------------------
SURFACE
STAB
!Nchordwise  Cspace  Nspanwise  Sspace
1            1.0     7          -2.0
YDUPLICATE 
0.0
TRANSLATE 
6.0  0.0  0.5
SECTION
!Xle    Yle    Zle     Chord   Ainc  Nspanwise  Sspace
-0.1    0.     0.0     0.4     0.    7          -1.25
CONTROL
elevator  1.0  0.0  0. 0. 0.  1

SECTION
!Xle    Yle    Zle     Chord   Ainc  Nspanwise  Sspace
-0.075  2.00   0.0     0.3     0.    0          0
CONTROL
elevator  1.0  0.0  0. 0. 0.  1

#--------------------------------------------------
SURFACE
FIN
!Nchordwise  Cspace   Nspanewise  Sspace
1            1.0      10          1.0
TRANSLATE
6.0   0.0  0.5
SECTION
!Xle    Yle    Zle     Chord   Ainc  Nspanwise  Sspace
-0.1    0.     0.0     0.4     0.    7          -1.25
CONTROL
rudder  1.0  0.0  0. 0. 0.  1

SECTION
!Xle    Yle    Zle     Chord   Ainc  Nspanwise  Sspace
-0.075  0.     1.0     0.3     0.    0          0
CONTROL
rudder  1.0  0.0  0. 0. 0.  1