# Panelmodel data file v0.5
# Part of Silent Wings
# Ola Rĝer Thorsen 02.07.02

aero_coordinate_system = true
reference_position     = [ 2.2 0.0 0.0 ]

#
# general things
#

plane_name		= Ventus2c 18m
plane_description	= 18m class

#cg = [ 2.35 0.0 0.0 ]

#
# Airfoil data. Note: these are "finite wing airfoils", not
# 2-dimensional data.
# Thus, normally an airfoil would only be shared by panels belonging
# to the same wing.

airfoil {
   name		= mainwing
   profile	= antares_wing
   k		= 0.96
   aspectratio	= 29.5
   meanchord	= 0.664
   cd_adjust    = -0.002
}

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

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

airfoil {
   name		= wing_tip
   profile	= antares_wing_tip
   k            = 0.96
   aspectratio  = 29.5
   meanchord    = 0.664
}

#
# And then the various panel settings...
#

# Panel number 1

wingpanel {
   name		= left wing tip
   airfoil	= wing_tip
   gfx_node     = wing flex control left outer
   area		= 1.48
   meanchord	= 0.3
   position	= [ 2.309 -7.134 0.8 ]
   alpha	= -2.0
   dihedral	= 6.0
   sweep	= 0.0
   delta_max	= 27.0
   delta_min	= -17.0
   delta_neutral = 0.0
   aileron_mix	= 1.0
   aileron_delta = 28.0
   flap_pos	= 25.0
   flap_neg	= -3.0
   diff_pos	= 2.8
   diff_neg	= 1.0
   elevator_mix	= 0.0
   brake_mix	= 0.0
   rudder_mix	= 0.0
   throttle_mix	= 0.0
}

wingpanel {
name		= right wing tip
airfoil		= wing_tip
gfx_node        = wing flex control right outer
area		= 1.48
meanchord	= 0.3
position	= [ 2.309 7.134 0.8 ]
alpha		= -2.0
dihedral	= -6.0
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
}

wingpanel {
name		= left wing middle
airfoil		= wing_tip
gfx_node        = wing flex control left middle
dep_panels      = [ "left wing tip" ]
area		= 1.56
meanchord	= 0.45
position	= [ 2.206 -4.444 0.52 ]
alpha		= 0.0
dihedral	= 3.5
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
}

wingpanel {
name		= right wing middle
airfoil		= wing_tip
gfx_node        = wing flex control right middle
dep_panels      = [ "right wing tip" ]
area		= 1.56
meanchord	= 0.45
position	= [ 2.206 4.444 0.52 ]
alpha		= 0.0
dihedral	= -3.5
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
}

wingpanel {
name		= left wing root
airfoil		= mainwing
gfx_node        = wing flex control left inner
dep_panels      = [ "left wing tip" "left wing middle" ]
area		= 2.5
meanchord	= 0.664
position	= [ 2.202 -1.606 0.357 ]
alpha		= 0.0
dihedral	= 3.0
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
}


wingpanel {
name		= right wing root
airfoil		= mainwing
gfx_node        = wing flex control right inner
dep_panels      = [ "right wing tip" "right wing middle" ]
area		= 2.5
meanchord	= 0.664
position	= [ 2.202 1.606 0.357 ]
alpha		= 0.0
dihedral	= -3.0
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
}

wingpanel {
name		= left airbrake
airfoil		= mainwing
area		= 0.95
meanchord	= 0.664
position	= [ 2.195 -2.631 0.416 ]
alpha		= 0.0
dihedral	= 3.0
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= 1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
brake_on	= 1
brake_surface	= 1.0
brake_height	= 0.2
brake_liftdest 	= 1.0
brake_cd	= 0.8
brake_superp	= 1
}

wingpanel {
name		= right airbrake
airfoil		= mainwing
area		= 0.95
meanchord	= 0.664
position	= [ 2.195 2.631 0.416 ]
alpha		= 0.0
dihedral	= -3.0
sweep		= 0.0
delta_max	= 27.0
delta_min	= -17.0
delta_neutral	= 0.0
aileron_mix	= -1.0
aileron_delta	= 28.0
flap_pos	= 25.0
flap_neg	= -3.0
aileron_diff    = 1.5
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
brake_on	= 1
brake_surface	= 1.0
brake_height	= 0.2
brake_liftdest 	= 1.0
brake_cd	= 0.8
brake_superp	= 1
}


wingpanel {
name		= elevator
airfoil		= elevator
area		= 1.01
meanchord	= 0.377
position	= [ 6.247 0.0 1.40 ]
alpha 		= -1.0
dihedral	= 0.0
sweep		= 0.0
delta_max	= 18.0
delta_min	= -25.0
delta_neutral	= 0.0
aileron_mix	= 0.0
aileron_delta	= 0.0
flap_pos	= 0.0
flap_neg	= 0.0
diff_pos	= 0.0
diff_neg	= 0.0
elevator_mix	= 1.0
brake_mix	= 0.0
rudder_mix	= 0.0
throttle_mix	= 0.0
flap_mix        = 0.15
propwash        = 0.3
}

wingpanel {
name		= rudder
airfoil		= rudder
area		= 1.14
meanchord	= 0.780
position	= [ 6.136 0.0 0.476 ]
alpha		= 0.0
dihedral	= 90.0
sweep		= 0.0
delta_max	= 30.0
delta_min	= -30.0
delta_neutral	= 0.0
aileron_mix	= 0.0
aileron_delta	= 0.0
flap_pos	= 0.0
flap_neg	= 0.0
diff_pos	= 0.0
diff_neg	= 0.0
elevator_mix	= 0.0
brake_mix	= 0.0
rudder_mix	= 1.0
throttle_mix	= 0.0
propwash        = 0.5
broken_drag     = 0.3
}


fuselage {
   name		= fuselage
   position	= [ 2.6940 0.0 0.0 ]
   ref_area	= 12.53
   ref_volume	= 1.0
   cd_front	= ventus2
   cd_side	= 0.05
   cd_top	= 0.05
   k_y		= 0.1
   k_z		= 0.1
   alpha_fuselage  = 0.0
   cd_landinggear  = 0.0015
}

