[smanist]

Hi guys,

I have just begun using SU2, which I hope I can use to simulate hypersonic flow with real gas effects. I assumed that is possible, because I noticed the existence of TNE2 module in SU2. I have tried the RAMC-II test case and ran a Mach 12 double-wedge airfoil case for Euler solution. They worked well.

However, when I try to get RANS solution of the double-wedge case, I get this error

------------------------------ Begin Solver -----------------------------

!!! Error: There is a NaN in the residual. Now exiting... !!!

In my case, I configured flow condition to be H=12km in atmosphere,

FREESTREAM_TEMPERATURE= 220.61
REYNOLDS_NUMBER= 8.07145E7
REYNOLDS_LENGTH= 1.0

The output of SU2 is correct, as it shows

Specific gas constant: 287.058 N.m/kg.K.
Free-stream pressure: 20646.1 Pa.
Free-stream temperature: 220.61 K.
Free-stream density: 0.326019 kg/m^3.
Free-stream velocity: (3573.08, 0) m/s. Magnitude: 3573.08 m/s.
Free-stream total energy per unit mass: 6.54177e+06 m^2/s^2.
Free-stream viscosity: 1.44323e-05 N.s/m^2.

For the rest of the configure file, the key settings are, (the whole file is just too long to be posted here)

PHYSICAL_PROBLEM= NAVIER_STOKES
KIND_TURB_MODEL= SA
VISCOSITY_MODEL= SUTHERLAND
MARKER_HEATFLUX= ( UPPER, 0.0, LOWER, 0.0 ) % Wall BC
MARKER_FAR= ( INLET, OUTLET ) % Farfield
CONV_NUM_METHOD_FLOW= ROE
SPATIAL_ORDER_FLOW= 2ND_ORDER
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
TIME_DISCRE_FLOW= EULER_IMPLICIT
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
SPATIAL_ORDER_TURB= 2ND_ORDER
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
TIME_DISCRE_TURB= EULER_IMPLICIT

I also tried Mach 2 (Re=1.34524E7), after several iterations, same issue happens. For Mach 3 (Re=2.01786E7), same thing, except that there is also a message,

There are 4 non-physical states in the upwind reconstruction.

I am still playing with the setting to see what happens. Any idea what might be wrong here? Any help will be appreciated.

Thank you in advance!
Danny