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February 22, 2024, 03:01 |
[NEMO] Divergence for two-directional flow
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#1 |
New Member
Jesslyn Ong
Join Date: Nov 2023
Posts: 4
Rep Power: 2 |
Hi pals!
I am trying to analyse Falcon 9 along its reentry trajectory. To simply the simulation, I'm having a simplified model with one nozzle at the moment in Argon environment. There are two main parts: 1. Descent w/o plume 2. Descent w plume For part 1, there are no issues with it and the results are fine. For part 2, I configure the Argon freestream and added MARKER_SUPERSONIC_INLET at the nozzle exit with negative x-velocity component but it diverges immediately. Code:
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% % % % SU2 configuration file % % Case description: Simplified Falcon 9 (Argon) % % Author: Jesslyn Ong % % Institution: Korea Advanced Institute of Science and Technology % % Date: 22.02.2024 % % File Version 8.0.0 "Harrier" % % % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% SOLVER= NEMO_NAVIER_STOKES MATH_PROBLEM= DIRECT SYSTEM_MEASUREMENTS= SI TIME_DOMAIN= NO CFL_NUMBER= 0.5 ITER= 50000 FLUID_MODEL= SU2_NONEQ GAS_MODEL= ARGON GAS_COMPOSITION= ( 1.0 ) FROZEN_MIXTURE= YES VISCOSITY_MODEL= SUTHERLAND CONDUCTIVITY_MODEL= CONSTANT_PRANDTL MACH_NUMBER= 4.675 INIT_OPTION= TD_CONDITIONS FREESTREAM_PRESSURE= 0.1129 FREESTREAM_TEMPERATURE= 198.6 FREESTREAM_TEMPERATURE_VE= 198.6 MARKER_FAR= ( FARFIELD, INLET ) MARKER_SMOLUCHOWSKI_MAXWELL= ( WALL, 300 ) MARKER_SUPERSONIC_INLET= ( NOZZLEEXIT, 1500, 3.55E+4, -3000, 0.0, 0.0 ) INLET_TEMPERATURE_VE= 1500 INLET_GAS_COMPOSITION= ( 1.0 ) MARKER_MONITORING= ( WALL ) MARKER_PLOTTING= ( WALL ) MARKER_ANALYZE= ( WALL ) REF_LENGTH= 13 REF_AREA= 0 NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES TRANSPORT_COEFF_MODEL= WILKE %CONV_NUM_METHOD_FLOW= ROE CONV_NUM_METHOD_FLOW= AUSMPLUSUP2 USE_ACCURATE_FLUX_JACOBIANS= YES TIME_DISCRE_FLOW= EULER_EXPLICIT MESH_FILENAME= 2dfull.su2 MESH_FORMAT= SU2 SOLUTION_FILENAME= restart_flow VOLUME_FILENAME= flow TABULAR_FORMAT= CSV OUTPUT_FILES= RESTART, PARAVIEW VOLUME_OUTPUT= ( COORDINATES, SOLUTION, PRIMITIVE, TIME_STEP ) HISTORY_OUTPUT= ( ITER, FLOW_COEFF, AERO_COEFF, HEAT, FLOW_COEFF_SURF, AERO_COEFF_SURF, HEAT_SURF ) CONV_FILENAME= history OUTPUT_WRT_FREQ= 50 WRT_RESTART_OVERWRITE= YES RESTART_SOL= NO RESTART_FILENAME= restart_flow.dat READ_BINARY_RESTART= YES Code:
------------------------------ Begin Solver ----------------------------- Simulation Run using the Single-zone Driver Error in "void CSolver::SetResidual_RMS(const CGeometry*, const CConfig*)": ------------------------------------------------------------------------- SU2 has diverged (NaN detected). ------------------------------ Error Exit ------------------------------- Mesh file: https://drive.google.com/file/d/1vtG...ew?usp=sharing |
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Tags |
divergence, nemo, supersonic flow, supersonic inlet |
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