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| 1 | +% PROBLEM DEFINITION |
| 2 | +% |
| 3 | +SOLVER= EULER |
| 4 | +REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_MACH |
| 5 | +MATH_PROBLEM= DIRECT |
| 6 | +RESTART_SOL= NO |
| 7 | + |
| 8 | +% FREE-STREAM DEFINITION |
| 9 | +% |
| 10 | +% We are translating the domain instead of having farfield velocity. |
| 11 | +% Note: The rotating frame is intended for 3D cases. To use the feature in a 2D case, |
| 12 | +% care must be taken with respect to the axes, e.g. to obtain a pitching motion, a |
| 13 | +% rotation about the z-axis can be used. |
| 14 | +GRID_MOVEMENT= ROTATING_FRAME |
| 15 | +MOTION_ORIGIN= 0.0, 0.0, 0.0 |
| 16 | +ROTATION_RATE= 0.0, 0.0, 0.0 |
| 17 | +TRANSLATION_RATE= -265.05707641411146, 0.0, 0.0 |
| 18 | +MACH_NUMBER= 0.0 |
| 19 | +FREESTREAM_PRESSURE= 101325.0 |
| 20 | +FREESTREAM_TEMPERATURE= 273.15 |
| 21 | + |
| 22 | +% REFERENCE VALUES |
| 23 | +% |
| 24 | +% The AOA is only needed to compute CD and CL, it should match the translation rate. |
| 25 | +AOA= 0.0 |
| 26 | +% Same for the Mach number of the motion. |
| 27 | +MACH_MOTION= 0.8 |
| 28 | +REF_ORIGIN_MOMENT_X= 0.00 |
| 29 | +REF_ORIGIN_MOMENT_Y= 0.00 |
| 30 | +REF_ORIGIN_MOMENT_Z= 0.00 |
| 31 | +REF_LENGTH= 1.0 |
| 32 | +REF_AREA= 1.0 |
| 33 | + |
| 34 | +% BOUNDARY CONDITIONS |
| 35 | +% |
| 36 | +MARKER_EULER= ( airfoil ) |
| 37 | +MARKER_FAR= ( farfield ) |
| 38 | +MARKER_PLOTTING= ( airfoil ) |
| 39 | +MARKER_MONITORING= ( airfoil ) |
| 40 | +% We are specifying this marker to have an easy way to access it in python. |
| 41 | +MARKER_DEFORM_MESH= ( airfoil ) |
| 42 | + |
| 43 | +% DISCRETIZATION METHODS |
| 44 | +% |
| 45 | +CONV_NUM_METHOD_FLOW= ROE |
| 46 | +MUSCL_FLOW= YES |
| 47 | +NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES |
| 48 | +SLOPE_LIMITER_FLOW= VENKATAKRISHNAN_WANG |
| 49 | +VENKAT_LIMITER_COEFF= 0.1 |
| 50 | + |
| 51 | +% SOLUTION ACCELERATION |
| 52 | +% |
| 53 | +CFL_NUMBER= 1e3 |
| 54 | +CFL_ADAPT= NO |
| 55 | +% |
| 56 | +MGLEVEL= 3 |
| 57 | +MGCYCLE= W_CYCLE |
| 58 | +% |
| 59 | +LINEAR_SOLVER= FGMRES |
| 60 | +LINEAR_SOLVER_PREC= ILU |
| 61 | +LINEAR_SOLVER_ERROR= 0.1 |
| 62 | +LINEAR_SOLVER_ITER= 10 |
| 63 | + |
| 64 | +% CONVERGENCE PARAMETERS |
| 65 | +% |
| 66 | +ITER= 250 |
| 67 | +CONV_FIELD= RMS_DENSITY |
| 68 | +CONV_RESIDUAL_MINVAL= -9 |
| 69 | + |
| 70 | +% INPUT/OUTPUT |
| 71 | +% |
| 72 | +MESH_FILENAME= ../../euler/naca0012/mesh_NACA0012_inv.su2 |
| 73 | +MESH_FORMAT= SU2 |
| 74 | +SCREEN_OUTPUT= (INNER_ITER, RMS_RES, FORCE_X, FORCE_Y, FORCE_Z, MOMENT_X, MOMENT_Y, MOMENT_Z) |
| 75 | +HISTORY_OUTPUT= (INNER_ITER, RMS_RES, AERO_COEFF) |
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