# Panelmodel for ASW27
# Ola Røer Thorsen
# Silent Wings AS
# (Beta version)

airfoil {
   name         = mw
   profile      = antares_wing
   k            = 0.95
   aspectratio  = 25.0
   meanchord    = 0.664
   cd_adjust    = -0.005
}

airfoil {
   name         = wt
   profile      = antares_wing_tip
   k            = 0.95
   aspectratio  = 25.0
   meanchord    = 0.664
   cd_adjust    = -0.005
}

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
}

# Wing definitions

wing {
name = main wing
position = [ 0.0 0.0 0.0 ]

geom_y         = [   0.0      0.35     3.97     4.6      7.37     7.5   ]
geom_x         = [   0.128    0.128    0.08     0.078   -0.2     -0.25  ]
geom_chord     = [   0.2      0.8      0.658    0.639    0.263    0.25  ]
geom_dihedral  = [   3.0      3.0      3.0      3.0      3.0      3.0   ]
geom_alpha     = [   0.5      0.5      0.5      0.5      0.5      0.5   ]
geom_airfoil   = [   "mw"     "mw"     "mw"     "mw"     "wt"     "wt"  ]

ctrl_y             = [   0.35    3.97    7.37 ]
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_flap_pos      = [       25.0    25.0    ]
ctrl_flap_neg      = [        0.0     0.0    ]
ctrl_flap_ctrl     = [        0       1      ]
ctrl_diff_pos      = [        1.5     1.5    ]
ctrl_diff_neg      = [        1.5     1.5    ]

spoiler_y_inner  = 2.182
spoiler_y_outer  = 3.396
spoiler_height   = 0.4
spoiler_liftdest = 1.5
spoiler_cd       = 0.9
}


wingpanel {
name            = elevator
airfoil         = elevator
area            = 1.55
meanchord       = 0.696
position        = [ -4.1 0.0 -1.338 ]
alpha           = -2.0
dihedral        = 0.0
delta_max       = 20.0
delta_min       = -20.0
delta_neutral   = 0.0
elevator_mix    = 1.0
}

wingpanel {
name            = rudder
dep_panels      = [ elevator ]
airfoil         = rudder
area            = 1.43
meanchord       = 0.89
position        = [ -4.1 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        = [ -2.3 0.0 0.0 ]
ref_area        = 12.53
ref_volume      = 1.0
cd_front        = antares
cd_side         = 0.01
cd_top          = 0.01
k_y             = 0.4
k_z             = 0.4
alpha_fuselage  = 0.0
cd_landinggear  = 0.005
}
