[marco.fossati]

Hi all,

I am trying to run a supersonic inviscid case over a space shuttle using the FREESTREAM_PRESS_EQ_ONE option.

I have issues with what is happening in the undisturbed region of the flow ahead the vehicle (see image attached).

Point is that if I run DIMENSIONAL the same region looks OK, except that afterwards the simulation diverges due to nonphysical solution in the rear part of the shuttle.

Before playing around with the mesh I would appreciate any comment on what could be wrong with my settings (see config file below)

Please note that I am already at CFL 0.01, and running first order

Thanks

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES)
PHYSICAL_PROBLEM= EULER
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
%
% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
%
% Regime type (COMPRESSIBLE, INCOMPRESSIBLE)
REGIME_TYPE= COMPRESSIBLE
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 3
%
% Angle of attack (degrees)
AoA= 180
%
% Side-slip angle (degrees)
SIDESLIP_ANGLE= 0.0
%
% Free-stream pressure (101325.0 N/m^2 by default, only for Euler equations)
FREESTREAM_PRESSURE= 101325
%
% Free-stream temperature (288.15 K by default)
FREESTREAM_TEMPERATURE= 288
%
% Reynolds number (non-dimensional, based on the free-stream values)
%REYNOLDS_NUMBER= 9.E6
%
% Reynolds length (1 m by default)
%REYNOLDS_LENGTH= 1
%
% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
%
% Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS)
FLUID_MODEL= STANDARD_AIR
%
% Ratio of specific heats (1.4 default and the value is hardcoded
% for the model STANDARD_AIR)
GAMMA_VALUE= 1.4
%
% Specific gas constant (287.058 J/kg*K default and this value is hardcoded
% for the model STANDARD_AIR)
GAS_CONSTANT= 287.058
%
% Critical Temperature (131.00 K by default)
CRITICAL_TEMPERATURE= 131.00
%
% Critical Pressure (3588550.0 N/m^2 by default)
CRITICAL_PRESSURE= 3588550.0
%
% Critical Density (263.0 Kg/m3 by default)
CRITICAL_DENSITY= 263.0
%
% Acentric factor (0.035 (air))
ACENTRIC_FACTOR= 0.035
%
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).
VISCOSITY_MODEL= SUTHERLAND
%
% Molecular Viscosity that would be constant (1.716E-5 by default)
MU_CONSTANT= 1.716E-5
%
% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)
MU_REF= 1.716E-5
%
% Sutherland Temperature Ref (273.15 K default value for AIR SI)
MU_T_REF= 273.15
%
% Sutherland constant (110.4 default value for AIR SI)
SUTHERLAND_CONSTANT= 110.4
%
% Specify turbulence model (NONE, SA, SA_NEG, SST)
KIND_TURB_MODEL= SST
%
% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
%
% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
% Molecular Thermal Conductivity that would be constant (0.0257 by default)
KT_CONSTANT= 0.0257
%
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional moment
REF_LENGTH_MOMENT= 1.0
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 0
%
% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE
%
% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
%
% Marker of the surface which is going to be plotted or designed
MARKER_PLOTTING= ( WING_UPPER, WING_LOWER, FUSELAGE, VERTICALFIN, NACELLE, RADOME, REAR, EXIT, SYMMETRYPLANE )
%
% Marker of the surface where the functional (Cd, Cl, etc.) will be evaluated
MARKER_MONITORING= ( WING_UPPER, WING_LOWER, FUSELAGE, VERTICALFIN, NACELLE, RADOME, REAR )
%
% Euler wall boundary marker(s) (NONE = no marker)
MARKER_EULER= ( WING_UPPER, WING_LOWER, FUSELAGE, VERTICALFIN, NACELLE, RADOME, REAR, SYMMETRYPLANE )
%
% Navier-Stokes (no-slip), constant heat flux wall marker(s) (NONE = no marker)
% Format: ( marker name, constant heat flux (J/m^2), ... )
MARKER_HEATFLUX= ( NONE )
%
% Navier-Stokes (no-slip), isothermal wall marker(s) (NONE = no marker)
% Format: ( marker name, constant wall temperature (K), ... )
MARKER_ISOTHERMAL= ( NONE )
%
% Far-field boundary marker(s) (NONE = no marker)
MARKER_FAR= ( NONE )
%
% Symmetry boundary marker(s) (NONE = no marker)
MARKER_SYM= ( NONE )
%
% Zone interface boundary marker(s) (NONE = no marker)
MARKER_INTERFACE= ( NONE )
%
% Actuator disk boundary marker(s) (NONE = no marker)
% Format: ( inlet face marker, outlet face marker,
% rotation_angle_x-axis, rotation_angle_y-axis, rotation_angle_z-axis,
% root radius, tip radius, pressure jump, temperature jump, rev/min,
% uniform(0)/linear(1) distribution, ... )
MARKER_ACTDISK= ( NONE )
%
% Inlet boundary type (TOTAL_CONDITIONS, MASS_FLOW)
INLET_TYPE= TOTAL_CONDITIONS
%
% Inlet boundary marker(s) with the following formats (NONE = no marker)
% Total Conditions: (inlet marker, total temp, total pressure, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
% Mass Flow: (inlet marker, density, velocity magnitude, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
% Incompressible: (inlet marker, NULL, velocity magnitude, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
MARKER_INLET= ( NONE )
%
% Supersonic inlet boundary marker(s) (NONE = no marker)
% Format: (inlet marker, temperature, static pressure, velocity_x,
% velocity_y, velocity_z, ... ), i.e. primitive variables specified.
MARKER_SUPERSONIC_INLET= ( FARFIELD, 288, 101325, -1020.625, 0.0, 0.0 )
%
% Outlet boundary marker(s) (NONE = no marker)
% Format: ( outlet marker, back pressure (static), ... )
MARKER_OUTLET= ( NONE )
%
% Supersonic outlet boundary marker(s) (NONE = no marker)
MARKER_SUPERSONIC_OUTLET= ( EXIT )
%
% Periodic boundary marker(s) (NONE = no marker)
% Format: ( periodic marker, donor marker, rotation_center_x, rotation_center_y, rotation_center_z, rotation_angle_x-axis, rotation_angle_y-axis, rotation_angle_z-axis, translation_x, translation_y, translation_z, ... )
MARKER_PERIODIC= ( NONE )
%
% Displacement boundary marker(s) (NONE = no marker)
% Format: ( displacement marker, displacement value normal to the surface, ... )
MARKER_NORMAL_DISPL= ( NONE )
%
% Pressure boundary marker(s) (NONE = no marker)
% Format: ( pressure marker )
MARKER_PRESSURE= ( NONE )
%
% Neumann bounday marker(s) (NONE = no marker)
MARKER_NEUMANN= ( NONE )
%
% Dirichlet boundary marker(s) (NONE = no marker)
MARKER_DIRICHLET= ( NONE )
%
% Riemann boundary marker(s) (NONE = no marker)
% Format: (marker, data kind flag, list of data)
MARKER_RIEMANN= ( NONE )
%
% Non Reflecting boundary conditions marker(s) (NONE = no marker)
% Format: (marker, data kind flag, list of data)
MARKER_NRBC= ( NONE )
%
% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
% Numerical method for computation of spatial gradients: (GREEN_GAUSS,
% WIEGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
% Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 0.01
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= NO
%
% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
% CFL max value )
CFL_ADAPT_PARAM= ( 1.5, 0.5, 0.5, 5.0 )
%
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
%
% Number of total iterations
EXT_ITER= 1000000
%
% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Min error of the linear solver for the implicit formulation
LINEAR_SOLVER_ERROR= 1E-6
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 30
%
% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
% Multi-Grid Levels (0 = no multi-grid)
MGLEVEL= 3
%
% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
MGCYCLE= W_CYCLE
%
% Multi-Grid PreSmoothing Level
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
%
% Multi-Grid PostSmoothing Level
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
%
% Jacobi implicit smoothing of the correction
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
%
% Damping factor for the residual restriction
MG_DAMP_RESTRICTION= 1.0
%
% Damping factor for the correction prolongation
MG_DAMP_PROLONGATION= 1.0
%
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= ROE
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_FLOW= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN, MINMOD)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% Coefficient for the limiter
LIMITER_COEFF= 0.3
%
% 1st, 2nd and 4th order artificial dissipation coefficients
AD_COEFF_FLOW= ( 0.15, 0.5, 0.04 )
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT
%

% --------------------------- CONVERGENCE PARAMETERS --------------------------&
%
% Convergence criteria (CAUCHY, RESIDUAL)
CONV_CRITERIA= RESIDUAL
%
% Residual reduction (order of magnitude with respect to the initial value)
RESIDUAL_REDUCTION= 6
%
% Min value of the residual (log10 of the residual)
RESIDUAL_MINVAL= -6
%
% Start convergence criteria at iteration number
STARTCONV_ITER= 100
%
% Number of elements to apply the criteria
CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CAUCHY_EPS= 1E-10
%
% Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY,
% SENS_MACH, DELTA_LIFT, DELTA_DRAG)
CAUCHY_FUNC_FLOW= DRAG
%