inputs updating {
  interval               = 1000
  schedulefile           = schedule.dat
  do schedule            = true
  trigger                = ctu
  do levels              = true
  do maxcells            = true
  do upwind blending min = true
}


# Specify fluid, LAVA provides a library of fluids
fluid {
  species = air_perfect
}

# List reference conditions.
# Everything in the inputs file is in SI units.
# Reference conditions are used as initial conditions
# and also for farfield boundary condition
# When alpha, beta is specified, the flow is setup in
# standard airplane axes, i.e downstream axis is +x
# up axis is +z, right wing is +y
# Alternatively, you can specify the flow velocities as a vector
# Also, instead of pressure, you can specify Reynolds number (as Re=)
# Note that Reynolds number would be based on the length scale provided
reference conditions {
  mach        = 0.2
  Re          = 5.9e6
  temperature = 288.15      # K
  alpha       = 19.7        # deg
  beta        = 0.00
  length      = 7.00532     # m
  area        = 191.844778  # Half Sref m2
  dx          = 16e-3
}

time {
  steady             = false
  initial cfl        = 0.5
  cfl                = 0.95
  maxdtgrowthfactor  = 1.05
  computecflinterval = 10
  finish ctu         = 30
}
solver defaults {
  explicit {
    method = ssprk33
  }
  #restart
  #{
  #  file = restart/Cart_restartLatest.hdf5
  #}
}

cartesian {
  navier stokes {
    viscous = true
  }
  convective terms {
    scheme                  = hwcns
    flux order              = 4
    interp order            = 3
    central components      = [none]
    upwind blending sensors = [ducros]
    fluxfunction            = keepg hlle
    limiter                 = none
  }
  turbulence {
    sgs model = vreman
  }

  trip time relaxation = 40. # a factor of dt
  # trip_1 : Wing Upper Near Root
  # trip_2 : Wing Upper Near Nacelle Pylon
  # trip_3 : Wing Upper Near Tip
  # trip_4 : Nacelle outer circle
  # trip_5 : Nacelle inner circle
  # trip_6 : Nacelle pylon
  # trip_7 : Htail LE upper
  # trip_8 : Htail LE lower
  # trip_9 : Vtail LE
  # trip_10: Fuse nose zplus
  # trip_11: Fuse nose zminus
  # trip_12: Fuse nose yplus
  trip_line_1  {dxscale = 1.;begin = [2.546070E+01, 3.052050E+00, 4.729215E+00];end = [2.618612E+01, 3.971736E+00, 4.802266E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_2  {dxscale = 1.;begin = [3.000402E+01, 8.994870E+00, 5.215469E+00];end = [3.083125E+01, 1.007270E+01, 5.302925E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_3  {dxscale = 1.;begin = [4.507610E+01, 2.900512E+01, 6.720341E+00];end = [4.536383E+01, 2.937944E+01, 6.747311E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_4  {dxscale = 1.;center = [24.861590843432634, 9.803591119112955, 2.3914368745527694];axis = [-0.998535326, -0.030048636, -0.044992013];radius = 1.8;segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_5  {dxscale = 1.;center = [25.215387395427886, 9.781733682555998, 2.4194252651721597];axis = [-0.993729501, 0.022842868, -0.109452649];radius = 1.4;segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_6  {dxscale = 2.;begin = [2.634552E+01, 9.469491E+00, 4.450000E+00];end = [2.633544E+01, 9.758339E+00, 4.450000E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_7  {dxscale = 2.;begin = [5.739016E+01, 1.680946E+00, 6.745135E+00];end = [6.467291E+01, 1.066800E+01, 7.780111E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_8  {dxscale = 2.;begin = [5.734611E+01, 1.690681E+00, 6.252033E+00];end = [6.465877E+01, 1.066800E+01, 7.645515E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_9  {dxscale = 2.;begin = [5.402829E+01, 4.588661E-01, 8.514268E+00];end = [6.378401E+01, 1.260798E-01, 1.842068E+01];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_10 {dxscale = 2.;begin = [2.519835E+00, 0.000000E+00, 5.436731E+00];end = [2.519835E+00, 4.400000E-01, 5.436731E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_11 {dxscale = 2.;begin = [2.519835E+00, 0.000000E+00, 4.627336E+00];end = [2.519835E+00, 4.400000E-01, 4.627336E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}
  trip_line_12 {dxscale = 2.;begin = [2.519835E+00, 4.400000E-01, 4.627336E+00];end = [2.519835E+00, 4.400000E-01, 5.436731E+00];segmentlength = 2;segmentskip = 3;segmentradius = 0.9;projectionmethod = closest;projectionmaxdistance = 3;}

  output {

    outputbufferintervalisos = 10000
    outputbufferintervalsurf = 10000

    #an example of time averaged outputs
    #timeaveraging { start ctu = 14; dosurface = true; dovolume = true; doexponentialmovingaverage = true; exponentialmovingaveragewindowctu = 10.0}

    monitor {
      reset if missing = true
      interval         = 100
      variables        = [nt, ctu, dt, maxcfl, maxmach, maxpressure, maxtemperature, minpressure, mintemperature, cl_airplane, cd_airplane, cmy_airplane, blocks_1*, numcel*, wallt, mups, mups_max, mups_long, elapsed, memory_gpu]   #blocks-> how many cartesian boxes there are per level
    }
    volume {
      interval  = 100000
      variables = [q, density, mach, mask, errormetric, ducrossensor]
    }
    surface {  variables = [q, wallmodel]; interval = 1000 }

    # cut planes
    surface probe_1  {cutpoint = [27.81, 0, 0];cutdirection = x;interval = 1000 }
    surface probe_2  {cutpoint = [30.099, 0, 0];cutdirection = x;interval = 1000 }
    surface probe_3  {cutpoint = [32.38, 0, 0];cutdirection = x;interval = 1000 }
    surface probe_4  {cutpoint = [37.72, 0, 0];cutdirection = x;interval = 1000 }
    surface probe_5  {cutpoint = [44.07, 0, 0];cutdirection = x;interval = 1000 }
    surface probe_6  {cutpoint = [0, 20.19, 0];cutdirection = y;interval = 1000 }
    surface probe_7  {cutpoint = [0, 5.08, 0];cutdirection = y;interval = 1000 } #A
    surface probe_8  {cutpoint = [0, 7.76, 0];cutdirection = y;interval = 1000 } #B
    surface probe_9  {cutpoint = [0, 10.18, 0];cutdirection = y;interval = 1000 } #C
    surface probe_10 {cutpoint = [0, 12.6, 0];cutdirection = y;interval = 1000 } #D
    surface probe_11 {cutpoint = [0, 15.15, 0];cutdirection = y;interval = 1000 } #E
    surface probe_12 {cutpoint = [0, 17.96, 0];cutdirection = y;interval = 1000 } #F
    surface probe_13 {cutpoint = [0, 20.76, 0];cutdirection = y;interval = 1000 } #G
    surface probe_14 {cutpoint = [0, 23.18, 0];cutdirection = y;interval = 1000 } #H
    surface probe_15 {cutpoint = [0, 26.37, 0];cutdirection = y;interval = 1000 } #I
    surface probe_16 {cutpoint = [0, 28.92, 0];cutdirection = y;interval = 1000 } #J


    isosurfaces_1{ point   = [0, 7.76, 0]; normal = [0, 1, 0]; format = vtk; interval = 1000; colorfield = errormetric   }
    isosurfaces_2{ point   = [0, 7.76, 0]; normal = [0, 1, 0]; format = vtk; interval = 1000; colorfield = densitygradmag   }
    isosurfaces_3{ contour = qcriterion; isovalue = 1e6; format = vtk; interval = 5000; colorfield = umag        } # iso-surface of q-criterion colored by velocity magnitude
    isosurfaces_4{ contour = qcriterion; isovalue = 1e5; format = vtk; interval = 5000; colorfield = umag        } # iso-surface of q-criterion colored by velocity magnitude


    restart {
      interval = 50000
    }
    flow_stats { }


    loads {
      moment center = [33.67786, 0.0, 4.51993]
      interval      = 100
      # Provide non-dimensional force and moments
      normalize = true
      # Use gauge pressure (p-p_ref) in pressure forces
      gauge = true
      group_1 {
        name = airplane
        # Which BC zones to include
        include = [1-28, 30-33]
      }
      group_2 {
        name = wing
        # Which BC zones to include
        include = [1-19]
      }
      group_3 {
        name = tail
        # Which BC zones to include
        include = [24-28, 30-33]
      }
      group_4 {
        name = wing_fuse
        # Which BC zones to include
        include = [1-23]
      }
    }
  }

  bcs {
    BC_1{type = wall; kind = [slip, wallstressmodel, blendedlog];components = [1-13, 15-33]; }
    BC_2{type = wall; kind = [slip, wallstressmodel, wmnoslip]; components = [14]}

    ibmethod = gcm
    gcmtype  = imagedist

    domain face type lo = [inlet, wall, inlet]
    domain face kind lo = [subsonic, slip, subsonic]
    domain face type hi = [outlet, extrapolation, outlet]
    domain face kind hi = [subsonic, constant, subsonic]
  }
  grid {
    finest dx = 0.004

    #   domain min = [-1048.576, 0.0,     -524.288]
    #   domain max = [ 1048.576, 1048.576, 524.288]
    targetfarfielddistance  = [1048.576, 1048.576, 524.288]
    aligndomainfacetoorigin = [none, lo, none]

    max box size    = 8                               # domain is partitioned into 8^3 boxes
    regrid interval = 5000

    solution based amr {
      method = auto
      max cells = 930000000                                   # AMR control: limits the number of cells within +/- 5%
      errormetricgeomdistancescalingreflength = 1.0
      errormetrictimemethod = avg                             # AMR control: use time-averaged error metric for mesh adapation
      errormetricexponentialmovingaveragewindowctu = 5.0   # AMR control: time scale over which to perform error metric averaging in convective time units (CTU)
      errormetricstatsinterval = 10                           # AMR control: how often to update statistics from instantaneous error metric
      regridgrowerrormetrictags = 1                           # AMR control: pad boxes scheduled to be refined from error metric by 1 to allow for longer intervals between adaption cycles
      errormetricthresholdratio = 0.5

      errormetric_1 {
        type   = smallscaleenergy
        weight = 1.0
      }

    }

    component tagging_1 {components = [2, 6, 10, 14, 15, 16, 18];dx = 0.004;type = component }
    component tagging_2 {components = [1, 3-5, 7-9, 11-13, 17, 19, 22-28, 30-33];dx = 0.008;type = component }
    component tagging_3 {components = [20-21];dx = 0.016;type = component }

  }
  # Components:
  # F  1: Nacelle_inner
  #XF  2: Wing_LE_Upper
  # F  3: Wing_TE_Upper
  # F  4: Wing_TE_Lower
  # F  5: Wing_LE_Lower
  #XF  6: Wing_flap_cove
  # F  7: Flap_track_fairings_connection
  # F  8: Flap_track_fairings_back
  # F  9: Nacelle_TE
  #XF 10: Nacelle_LE
  # F 11: Wing_Lower
  # F 12: Wing_Upper
  # F 13: Nacelle_outer
  #XF 14: Slats
  #XF 15: Flaps
  #XF 16: Vortex_generator
  # F 17: Nacelle_pylon
  #XF 18: Slat_attachments
  # F 19: Flap_track_fairings_front
  # M 20: Fuse_fairing
  # M 21: Fuse_aft
  # F 22: Fuse_forward
  # F 23: Fuse_nose
  # F 24: HTail_TE
  # F 25: HTail_LE
  # F 26: HTail_upper
  # F 27: HTail_lower
  # F 28: HTail_tip
  # C 29: Standoff
  # F 30: VTail_TE
  # F 31: VTail_LE
  # F 32: VTail
  # F 33: VTail_tip

  geometry {
    surfaces_1 {
      file name = 2p4_ONERA_LDG_v28.fro
    }
  }
}