# Title
RG 15A-1.8/11.0 airfoil, inviscid grid, 256x48 cells
#
# Grid file (in)
rg15a.grd
#
# Grid topology (in)
rg15a.top
#
# Flow field to plot (out); 5 digit iteration number and .v2d will be added
rg15a_iso_r
#
# Surface quantities to plot (out); 5 digit iter. number and .v2d will be added
rg15a_surf_r
#
# Convergence history (out); .v2d will be added
rg15a_conv_r
#
# Restart solution (in)
solin
#
# Restart solution (out)
solout
#
# Physics - general
# -----------------
 E         # E=external flow, I=internal flow
 E         # E=Euler (inviscid) / N=Navier-Stokes (laminar)
 1.4       # ratio of specific heats
 1004.5    # specific heat coeff. at constant pressure [J/kgK]
 1.e+6     # Reynolds number
 0.0       # reference velocity (internal flow only) [m/s]
 0.0       # reference density (internal flow only) [kg/m^3]
 0.72      # laminar Prandtl number
#
# Physics - external flow
# -----------------------
 0.01      # Mach-number at infinity
 2.0       # angle of attack [deg]
 1.E+5     # static pressure at infinity [Pa]
 288.0     # static temperature at infinity [K]
#
# Physics - internal flow
# -----------------------
 0.0       # total pressure at inlet [Pa]
 0.0       # total temperature at inlet [K]
 0.0       # flow angle at inlet (with x-axis) [deg]
 0.0       # static pressure at outlet [Pa]
 0.0       # approximate flow angle at outlet (with x-axis) [deg]
 1.0       # approximate ratio of inlet to outlet static pressure
#
# Physics - injection boundary
# ----------------------------
 0.0       # mass flow rate [kg/m^2*s]
 0.0       # injection temperature [K]
#
# Geometrical reference values
# ----------------------------
 0.25      # x-coordinate of reference point (moment coefficient) [m]
 0.0       # y-coordinate            - '' -                       [m]
 1.0       # reference or chord length [m]
#
# Iteration control
# -----------------
 3000      # max. number of iterations
 99999     # number of iterations between solution dumps
 1.0E-5    # convergence tolerance
 N         # use previous solution for restart (Y=yes, N=no)
#
# Numerical parameters
# --------------------
 5.0       # CFL-number
 1.0       # coefficient of implicit residual smoothing (<0 = no smoothing)
 L         # L=local, G=global time-stepping
 Y         # low Mach-number preconditioning (Y=yes, N=no)
 0.5       # preconditioning parameter K
 R         # central scheme (C) or Roe's upwind scheme (R)
 0.0       # artificial dissipation coefficient - k2
 256.0     # artificial dissipation coefficient - 1/k4
 2         # 1st-order (1) / 2nd-order (2) Roe scheme
 100.0     # limiter coefficient (Roe's scheme)
 0.005     # entropy correction coefficient (Roe's scheme)
 Y         # correction of far-field due to single vortex (Y/N - external flow)
 3         # pressure extrapolation to walls (2- or 3-point formula)
 1.0       # max. rel. change of rho and rho*E at dummy cells of slip walls
 0.2       # max. rel. change of rho and rho*E at dummy cells of injection b.
 5         # number of stages
 0.0695, 0.1602, 0.2898, 0.5060, 1.000    # stage coefficients (Roe scheme)
 1.00  , 1.00  , 1.00  , 1.00  , 1.00     # dissipation blending coeff.
 1     , 1     , 1     , 1     , 1        # dissipation evaluation (1=yes)
#
# Quantities to plot (Y=yes, N=no)
# --------------------------------
 Y   # density
 Y   # u-velocity
 Y   # v-velocity
 Y   # static pressure
 N   # total pressure
 Y   # static temperature
 N   # total temperature
 Y   # local Mach-number
 N   # isentropic Mach-number
 N   # total pressure loss
 N   # laminar viscosity (only if present)
 N   # skin friction coefficient (boundaries only)
 Y   # pressure coefficient (boundaries only)

##############################################################################

 0.2500, 0.1667, 0.3750, 0.5000, 1.000    # stage coefficients (central scheme)
 1.00  , 0.00  , 0.56  , 0.00  , 0.44     # dissipation blending coeff.
 1     , 0     , 1     , 0     , 1        # dissipation evaluation (1=yes)

 0.0695, 0.1602, 0.2898, 0.5060, 1.000    # stage coefficients (Roe scheme)
 1.00  , 1.00  , 1.00  , 1.00  , 1.00     # dissipation blending coeff.
 1     , 1     , 1     , 1     , 1        # dissipation evaluation (1=yes)

 0.2742, 0.2067, 0.5020, 0.5142, 1.000    # stage coefficients (Roe scheme, viscous)
 1.00  , 0.00  , 0.56  , 0.00  , 0.44     # dissipation blending coeff.
 1     , 0     , 1     , 0     , 1        # dissipation evaluation (1=yes)
