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

# reference_position     = [ 2.9 0.0 0.0 ]

# General things

plane_name		= HK-36 Super Dimona
plane_description	= TMG

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

airfoil {
   name		= mainwing
   profile	= e603
   k		= 1.15
   aspectratio	= 17.43
   meanchord	= 0.93
   cd_adjust    = 0.0
}

airfoil {
   name		= elevator
   profile	= du86137
   k		= 1.2
   aspectratio	= 5.31
   meanchord	= 0.62
   cd_adjust    = 0.0
}

airfoil {
   name		= rudder
   profile	= fx71l150_30
   k		= 1.4
   aspectratio	= 1.857
   meanchord	= 0.780
   cd_adjust    = 0.0
}

# The panels

wing {
name = main wing

position = [ 0.5 0.0 0.0 ]

geom_y        = [   0.0    8.65  ]
geom_x        = [   0.0    0.0   ]
geom_chord    = [   1.2    0.8   ]
geom_dihedral = [   3.0    3.0   ]
geom_alpha    = [   0.0    0.0   ]
geom_airfoil  = [ "mainwing" "mainwing" ]

ctrl_y             = [   3.0     4.0     8.0 ]
ctrl_delta_max     = [       27.0    27.0    ]
ctrl_delta_min     = [      -17.0   -17.0    ]
ctrl_neutral       = [        0.0     0.0    ]
ctrl_aileron_mix   = [        1.0     1.0    ]
ctrl_aileron_delta = [       28.0    28.0    ]
ctrl_diff_pos      = [        1.5     1.5    ]
ctrl_diff_neg      = [        1.5     1.5    ]

spoiler_y_inner  = 2.3
spoiler_y_outer  = 5.3
spoiler_height   = 0.2
spoiler_liftdest = 1.0
spoiler_cd       = 0.9
}


wingpanel {
name		= elevator
airfoil		= elevator
area		= 2.05
meanchord	= 0.696
position	= [ -5.0 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	= [ -5.0 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	= [ 0.0 0.0 0.0 ]
ref_area	= 12.53
ref_volume	= 1.0
cd_front	= dimona
cd_side	        = 0.03
cd_top	        = 0.03
k_y		= 0.4
k_z		= 0.4
alpha_fuselage  = 5.0
}

