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

aero_coordinate_system = true
reference_position     = [ 2.19742 0.0 0.0 ]

# general info
plane_name		= Antares 20m
plane_description	= Electric selflaunching sailplane

# Airfoil data. 
airfoil {
   name		= mainwing
   profile	= antares_wing
   k		= 0.95
   aspectratio	= 33.37
   meanchord	= 0.664
   cl_adjust    = 1.2
}

airfoil {
   name		= wing_tip
   profile	= antares_wing_tip
   k            = 0.95
   aspectratio  = 33.37
   meanchord    = 0.664
   cl_adjust    = 1.2
}

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

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


# Panel number 1

wingpanel {
name		= left wing tip
airfoil         = wing_tip
gfx_node        = wing flex control left outer
area		= 0.382
meanchord	= 0.3
position	= [ 2.44047 -9.39654 0.6617 ]
alpha	        = 0.0
dihedral	= 3.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral   = 0.0
aileron_mix	= 1.0
aileron_delta   = 28.0
flap_pos	= 18.0
flap_neg	= -3.0
diff_pos	= 2.6
diff_neg	= 1.0
}

wingpanel {
name		= left wing middle
airfoil		= wing_tip
gfx_node        = wing flex control left middle
dep_panels      = [ "left wing tip" ]
area		= 2.1317
meanchord	= 0.45
position	= [ 2.27065 -6.74864 0.5232 ]
alpha		= 0.0
dihedral	= 3.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 28.0
flap_pos	= 18.0
flap_neg	= -3.0
diff_pos	= 2.6
diff_neg	= 1.0
brake_on	= 1
brake_surface	= 0.85
brake_height	= 0.2
brake_liftdest 	= 1.0
#brake_cd	= 1.2
brake_cd        = 0.9
brake_superp	= 0
}

wingpanel {
name		= left wing root
airfoil		= mainwing
gfx_node        = wing flex control left inner
dep_panels      = [ "left wing tip" "left wing middle" ]
#area		= 3.5362
area		= 4.0
meanchord	= 0.664
position	= [ 2.19742 -2.59962 0.306 ]
alpha		= 0.0
dihedral	= 3.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 28.0
flap_pos	= 18.0
flap_neg	= -3.0
diff_pos	= 2.6
diff_neg	= 1.0
}


wingpanel {
name		= right wing tip
airfoil		= wing_tip
gfx_node        = wing flex control right outer
area		= 0.382
meanchord	= 0.3
position	= [ 2.44047 9.39654 0.6617 ]
alpha		= 0.0
dihedral	= -3.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 18.0
flap_neg	= -3.0
diff_pos	= 2.6
diff_neg	= 1.0
}

wingpanel {
name		= right wing middle
airfoil		= wing_tip
gfx_node        = wing flex control right middle
dep_panels      = [ "right wing tip" ]
area		= 2.1317
meanchord	= 0.45
position	= [ 2.27065 6.74864 0.5232 ]
alpha		= 0.0
dihedral	= -3.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 18.0
flap_neg	= -3.0
diff_pos	= 2.6
diff_neg	= 1.0
brake_on	= 1
brake_surface	= 0.85
brake_height	= 0.2
brake_liftdest 	= 1.0
#brake_cd	= 1.2
brake_cd	= 0.9
brake_superp	= 0
}

wingpanel {
name		= right wing root
airfoil		= mainwing
gfx_node        = wing flex control right inner
dep_panels      = [ "right wing tip" "right wing middle" ]
#area		= 3.5362
area		= 4.0
meanchord	= 0.664
position	= [ 2.19742 2.59962 0.306 ]
alpha		= 0.0
dihedral	= -3.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 18.0
flap_neg	= -3.0
diff_pos	= 2.6
diff_neg	= 1.0
}

wingpanel {
name		= elevator
airfoil		= elevator
area		= 1.067
meanchord	= 0.377
position	= [ 6.7800 0.0 1.4400 ]
alpha 		= -1.0
dihedral	= 0.0
sweep		= 0.0
delta_max	= 18.0
delta_min	= -18.0
delta_neutral	= 0.0
elevator_mix	= 1.0
flap_mix        = 0.3
propwash        = 0.5
}

wingpanel {
name		= rudder
airfoil		= rudder
#area		= 1.1524
area            = 1.5
meanchord	= 0.780
position	= [ 6.809 0.0 0.6960 ]
alpha		= 0.0
dihedral	= 90.0
sweep		= 0.0
delta_max	= 30.0
delta_min	= -30.0
delta_neutral	= 0.0
rudder_mix	= 1.0
propwash        = 0.5
broken_drag     = 0.3
}

fuselage {
name		= fuselage
#position	= [ 2.6940 0.0 0.0 ]
position	= [ 2.3 0.0 0.0 ]
ref_area	= 12.53
ref_volume	= 1.0
cd_front	= antares
cd_side	        = 0.03
cd_top	        = 0.03
k_y		= 0.1
k_z		= 0.1
alpha_fuselage 	= 0.0
cd_landinggear = 0.005
}

