// ############################################################
// Onera M6 case from the Langley turbulence modeling site
// https://turbmodels.larc.nasa.gov/onerawingnumerics_val.html
// ############################################################

fluid {
  species = air_perfect
}

reference conditions {
  mach        = 0.84
  Re          = 14.6e6
  alpha       = 3.06
  temperature = 300
  beta        = 0.
  length      = 0.649749105896 # Mean Aerodynamic Chord (MAC)
  area        = 0.757500689023 # Semi-span area
}

unst {

  grid {
    file = onera_m6.cgns
  }

  convergence {
    relative tolerance = 1.e-8
  }

  implicit {
    number of steps   = 500
    jacobian interval = 5
    adaptive {
      min cfl            = 1.
      max cfl            = 100
      max cfl turbulence = 100
    }
  }

  convective terms {
    order         = 2
    limiter       = minmod
    flux function = ausmpw+
  }

  navierstokes {
    viscous                  = true
    maximum iterations       = 20
    density change threshold = 0.1
    jacobian method          = analytical
  }

  turbulence {
    model              = sa
    maximum iterations = 10
    jacobian method    = numerical
  }

  output {

    monitor {
      variables = [ns, l2resr0, l2turbresr0, cfl, maxmach, linits, linres, linitsturb, linresturb, cl_wing, cd_wing, elapsed]
    }

    volume {
      format    = cgns
      interval  = 500
      variables = [q, density, mach, eddyviscosity, viscosity, residuals]
    }

    restart {
      interval = 500
    }

    surface {
      interval  = 100
      variables = [q, mach, eddyviscosity, tauw, pcoef, cf, yplus]
    }

    loads {
      interval      = 1
      moment center = [0., 0., 0.]
      normalize     = true
      gauge         = true;
      group_1 {name = wing; include = [3]}
    }
  }

  # BC_1 : farfield
  # BC_2 : symmetry
  # BC_3 : wing

  BC_1 {type = farfield}
  BC_2 {type = symmetry}
  BC_3 {type = wall}

}