# Panelmodel data file 
# Part of Silent Wings
# Ola Rĝer Thorsen 25.10.2004

aero_coordinate_system = true
reference_position     = [ 2.9 0.0 0.0 ]

# General things

plane_name		= G-103IIA
plane_description	= Twin II Acro trainer

# The centre of gravity

#cg		= [ 2.9 0.0 0.0 ]

# Airfoil data. Note: these are "finite wing airfoils", not
# 2-dimensional data.

airfoil {
   name		= mainwing
   profile	= e603
   k		= 1.15
   aspectratio	= 17.1
   meanchord	= 1.02
   cd_adjust    = -0.006
}

airfoil {
   name		= elevator
   profile	= du86137
   k		= 1.2
   aspectratio	= 5.31
   meanchord	= 0.62
   cd_adjust    = -0.012
}

airfoil {
   name		= rudder
   profile	= fx71l150_30
   k		= 1.4
   aspectratio	= 1.857
   meanchord	= 0.780
   cd_adjust    = -0.012
}

# The panels

wingpanel {
name		= left wing tip
airfoil		= mainwing
gfx_node	= wing flex control left outer
area		= 3.1892
meanchord	= 0.837
position	= [ 2.776 -6.846 0.251 ]
alpha		= -1.0
dihedral	= 3.0
delta_max	= 25.0
delta_min	= -25.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 30.0
aileron_diff    = 1.5
}

wingpanel {
name		= left airbrake
airfoil		= mainwing
gfx_node	= airbrake control left
area		= 2.8
meanchord	= 1.225
position	= [ 2.873 -3.5 0.03 ]
alpha		= 0.0
dihedral	= 3.0
brake_on	= 1
brake_surface	= 0.65
brake_height	= 0.4
brake_liftdest 	= 1.0
brake_cd	= 1.3
brake_superp	= 1
}

wingpanel {
name		= left wing root
dep_panels	= [ "left wing tip" "left airbrake" ]
airfoil		= mainwing
gfx_node	= wing flex control left inner
area		= 6.1847
meanchord	= 1.225
position	= [ 2.873 -2.428 0.020 ]
alpha		= 0.0
dihedral	= 3.0
}

wingpanel {
name		= right wing tip
airfoil		= mainwing
gfx_node	= wing flex control right outer
area		= 3.1892
meanchord	= 0.837
position	= [ 2.776 6.846 0.251 ]
alpha		= -1.0
dihedral	= -3.0
delta_max	= 25.0
delta_min	= -25.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 30.0
aileron_diff    = 1.5
}

wingpanel {
name		= right airbrake
airfoil		= mainwing
gfx_node	= airbrake control right
area		= 2.8
meanchord	= 1.225
position	= [ 2.873 3.5 0.03 ]
alpha		= 0.0
dihedral	= -3.0
brake_on	= 1
brake_surface	= 0.65
brake_height	= 0.4
brake_liftdest 	= 1.0
brake_cd	= 1.3
brake_superp	= 1
}


wingpanel {
name		= right wing root
dep_panels	= [ "right wing tip" "right airbrake" ]
airfoil		= mainwing
gfx_node	= wing flex control right inner
area		= 6.1847
meanchord	= 1.225
position	= [ 2.873 2.428 0.020 ]
alpha		= 0.0
dihedral	= -3.0
}

wingpanel {
name		= elevator
airfoil		= elevator
area		= 2.05
meanchord	= 0.696
position	= [ 7.790 0.0 1.338 ]
alpha 		= -4.0
dihedral	= 0.0
delta_max	= 20.0
delta_min	= -25.0
delta_neutral	= 0.0
elevator_mix	= 1.0
}

wingpanel {
name		= rudder
dep_panels      = [ elevator ]
airfoil		= rudder
area		= 1.43
meanchord	= 0.89
position	= [ 7.498 0.0 0.628 ]
alpha		= 0.0
dihedral	= 90.0
delta_max	= 30.0
delta_min	= -25.0
delta_neutral   = 0.0
rudder_mix	= 1.0
broken_drag     = 0.3
}

fuselage {
name		= fuselage
#position	= [ 2.63 0.0 0.0 ]
position	= [ 2.3 0.0 0.0 ]
#position	= [ 2.0 0.0 0.0 ]
ref_area	= 12.53
ref_volume	= 1.0
cd_front	= twin2
cd_side	        = 0.03
cd_top	        = 0.03
k_y		= 0.4
k_z		= 0.4
alpha_fuselage  = 5.0
}

