0          --> =0 2D, =1 AXISYMMETRIC0          --> =0 Euler, =1 Navier-Stokes1.e2       --> Reynolds by meter (the mesh is given in meter)0.         --> inverse of Froude number (=0 no gravity)0.96        --> inflow Mach number1.         --> ratio pout/pin1          --> wall =1 newmann b.c.(adiabatic wall), =2 (isothermal wall)300.       --> inflow temperature (in Kelvin) for Sutherland laws288.       --> if isothermal walls , wall temperature (in Kelvin)0.0        --> angle of attack1          --> Euler fluxes =1 roe, =2 osher,=3 kinetic3          --> nordre = 1st order scheme, =2 2ndorder, =3 limited 2nd order1          --> =0 global time steping (unsteady), =1 local Euler, =2 local N.S.1.        --> cfl LastIteration --> number of time step500        --> frequence for the  solution to be saved1.e10      --> maximum physical time for run (for unsteady problems)-4.        --> order of magnitude for the residual to be reduced (for steady problems)INIT        --> =0 start with uniform solution, =1 restart from INIT_NScccc  turbulence  ccccccccccccccccccccccccccccccccccccccccccccccccccccccc0          --> =0 no turbulence model, =1 k-epsilon model0          --> =0 two-layer technique, =1 wall laws1.e-2      --> delta in wall laws or limit of the one-eq. model. (in meter)0          --> =0 start from uniform solution for k-epsilon, =1 from INIT_KE-1.e10 1.e10 -1.e10 1.e10    --> xtmin,xtmax,ytmin,ytmax (BOX for k-epsilon r.h.s)