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

aero_coordinate_system = true
reference_position     = [ 2.088 0.0 0.0 ]
#reference_position     = [ 2.254 0.0 0.0 ]

#
# general things
#

plane_name		= LS8
plane_description	= 15m std class

#cg		= [ 2.37 0.0 0.0 ]

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

airfoil {
   name		= mainwing
   profile	= ls8_wing
   k		= 0.95
   aspectratio	= 21.43
   meanchord	= 0.664
   cd_adjust    = -0.01
}

airfoil {
   name		= elevator
   profile	= du86137
   k		= 1.2
   aspectratio	= 7.61
   meanchord	= 0.377
}

airfoil {
   name 	= rudder
   profile      = std_rudder
   k		= 1.2
   aspectratio	= 1.857
   meanchord	= 0.780
}

# Panel number 1

wingpanel {
name		= left wing outer
gfx_node	= wing flex control left outer
airfoil		= mainwing
area		= 2.55
meanchord	= 0.664
position	= [ 2.099 -5.22 0.514 ]
alpha		= 0.0
dihedral	= 3.0
delta_max	= 20.0
delta_min	= -20.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 30.0
}

wingpanel {
name		= left airbrake
gfx_node	= airbrake control left
airfoil		= mainwing
area		= 1.3
meanchord	= 0.664
position	= [ 2.092 -3.19 0.380 ]
alpha		= 1.0
dihedral	= 3.0
brake_on	= 1
brake_surface	= 0.4
brake_height	= 0.2
brake_liftdest 	= 1.0
brake_cd	= 1.0
brake_superp	= 1
}

wingpanel {
name		= left wing root
dep_panels	= [ "left wing tip" "left airbrake" ]
gfx_node	= wing flex control left inner
airfoil		= mainwing
area		= 2.85
meanchord	= 0.664
position	= [ 2.088 -1.652 0.275 ]
alpha		= 2.0
dihedral	= 3.0
}


wingpanel {
name		= right wing outer
gfx_node	= wing flex control right outer
airfoil		= mainwing
area		= 2.55
meanchord	= 0.664
position	= [ 2.099 5.22 0.514 ]
alpha		= 0.0
dihedral	= -3.0
delta_max	= 20.0
delta_min	= -20.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 30.0
}

wingpanel {
name		= right airbrake
gfx_node	= airbrake control right
airfoil		= mainwing
area		= 1.3
meanchord	= 0.664
position	= [ 2.092 3.19 0.380 ]
alpha		= 1.0
dihedral	= -3.0
brake_on	= 1
brake_surface	= 0.4
brake_height	= 0.2
brake_liftdest 	= 1.0
brake_cd	= 1.0
brake_superp	= 1
}

wingpanel {
name		= right wing root
dep_panels	= [ "right wing tip" "right airbrake" ]
gfx_node	= wing flex control right inner
airfoil		= mainwing
area		= 2.85
meanchord	= 0.664
position	= [ 2.088 1.652 0.275 ]
alpha		= 2.0
dihedral	= -3.0
}


wingpanel {
name		= elevator
airfoil		= elevator
area		= 1.093
meanchord	= 0.4
position	= [ 6.329 0.0 1.123 ]
alpha 		= -2.0
dihedral	= 0.0
sweep		= 0.0
delta_max	= 16.0
delta_min	= -20.0
delta_neutral	= 0.0
elevator_mix	= 1.0
broken_drag     = 0.1
}

wingpanel {
name		= rudder
airfoil		= rudder
area		= 1.001
meanchord	= 1.0
position	= [ 6.057 0.0 0.522 ]
alpha		= 0.0
dihedral	= 90.0
sweep		= 0.0
delta_max	= 25.0
delta_min	= -25.0
delta_neutral	= 0.0
rudder_mix	= 1.0
broken_drag     = 0.3
}

fuselage {
name		= fuselage
position	= [ 2.4 0.0 0.0 ]
ref_area	= 12.53
ref_volume	= 1.0
cd_front	= ls8
cd_side		= 0.01
cd_top		= 0.01	
k_y		= 0.1
k_z		= 0.1
alpha_fuselage 	= 3.0
cd_landinggear  = 0.0015
}

