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Adding testcase for gust in combination with mesh deformation by using
the SU2-internal option SURFACE_MOVEMENT= DEFORMING
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‎TestCases/gust/gust_with_mesh_deformation.cfg‎

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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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% Solver type (EULER, NAVIER_STOKES, RANS,
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% INC_EULER, INC_NAVIER_STOKES, INC_RANS,
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% NEMO_EULER, NEMO_NAVIER_STOKES,
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% FEM_EULER, FEM_NAVIER_STOKES, FEM_RANS, FEM_LES,
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% HEAT_EQUATION_FVM, ELASTICITY)
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SOLVER= EULER
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%
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% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
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MATH_PROBLEM= DIRECT
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%
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% ------------------------------- SOLVER CONTROL ------------------------------%
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%
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% Maximum number of inner iterations
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INNER_ITER= 100
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%
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% Min value of the residual (log10 of the residual)
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CONV_RESIDUAL_MINVAL= -6
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%
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% Start convergence criteria at iteration number
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CONV_STARTITER= 0
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%
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% ------------------------- UNSTEADY SIMULATION -------------------------------%
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%
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TIME_DOMAIN=YES
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TIME_MARCHING= DUAL_TIME_STEPPING-2ND_ORDER
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TIME_STEP= 0.001
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TIME_ITER= 26
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%
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% --------------------------- GUST SIMULATION ---------------------------------%
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%
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% The gust simulation requires the GRID_MOVEMENT flag to be set to YES.
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% and the GRID_MOVEMENT_KIND to be set to GUST or any of the other options.
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% Apply a wind gust (NO, YES)
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GRID_MOVEMENT=GUST
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WIND_GUST= YES
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GUST_TYPE= ONE_M_COSINE
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GUST_DIR= Y_DIR
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GUST_WAVELENGTH= 10.0
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GUST_PERIODS= 1.0
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% Gust amplitude corresponds to ~2.0 deg AoA
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GUST_AMPL= 1.0
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%
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GUST_BEGIN_TIME= 0.0
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GUST_BEGIN_LOC=-10.0
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% --------------------------- MESH DEFORMATION--------------------------------%
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% Type of dynamic surface movement (NONE, DEFORMING, MOVING_WALL,
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% AEROELASTIC, AEROELASTIC_RIGID_MOTION EXTERNAL, EXTERNAL_ROTATION)
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SURFACE_MOVEMENT= DEFORMING
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%
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% Moving wall boundary marker(s) (NONE = no marker, ignored for RIGID_MOTION)
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MARKER_MOVING= ( airfoil )
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%
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% Plunging angular freq. (rad/s) in x, y, & z directions
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SURFACE_PLUNGING_OMEGA= 0.0 125.6 0.0
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%
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% Plunging amplitude (m or ft) in x, y, & z directions
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SURFACE_PLUNGING_AMPL= 0.0 0.001 0.0
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%
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% Move Motion Origin for marker moving (1 or 0)
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MOVE_MOTION_ORIGIN = 0
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% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
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%
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% Mach number (non-dimensional, based on the free-stream values)
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MACH_NUMBER= 0.2
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%
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% Angle of attack (degrees, only for compressible flows)
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AOA= 0.0
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%
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% Side-slip angle (degrees, only for compressible flows)
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SIDESLIP_ANGLE= 0.0
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%
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% Free-stream option to choose between density and temperature (default) for
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% initializing the solution (TEMPERATURE_FS, DENSITY_FS)
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FREESTREAM_OPTION= DENSITY_FS
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%
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% Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default)
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FREESTREAM_PRESSURE= 101325.0
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%
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% Free-stream density (1.2886 Kg/m^3, 0.0025 slug/ft^3 by default)
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FREESTREAM_DENSITY= 1.225
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%
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% Free-stream temperature (288.15 K, 518.67 R by default)
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FREESTREAM_TEMPERATURE= 288.15
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%
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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% Reference origin for moment computation (m or in)
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REF_ORIGIN_MOMENT_X = 0.25
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REF_ORIGIN_MOMENT_Y = 0.00
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REF_ORIGIN_MOMENT_Z = 0.00
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%
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% Reference length for moment non-dimensional coefficients (m or in)
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REF_LENGTH= 1.0
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%
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% Reference area for non-dimensional force coefficients (0 implies automatic
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% calculation) (m^2 or in^2)
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REF_AREA= 1.0
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%
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% Aircraft semi-span (0 implies automatic calculation) (m or in)
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SEMI_SPAN= 1.0
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%
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% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
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% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
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REF_DIMENSIONALIZATION= DIMENSIONAL
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% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
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%
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% Euler wall boundary marker(s) (NONE = no marker)
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% Implementation identical to MARKER_SYM.
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MARKER_EULER= ( airfoil )
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%
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% Far-field boundary marker(s) (NONE = no marker)
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MARKER_FAR= ( farfield )
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% ------------------------ SURFACES IDENTIFICATION ----------------------------%
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%
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% Marker(s) of the surface in the surface flow solution file
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MARKER_PLOTTING = ( airfoil )
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%
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% Marker(s) of the surface where the non-dimensional coefficients are evaluated.
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MARKER_MONITORING = ( airfoil )
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% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
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%
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% CFL number (initial value for the adaptive CFL number)
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CFL_NUMBER= 100.0
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%
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% Adaptive CFL number (NO, YES)
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CFL_ADAPT= YES
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%
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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%
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% Multi-grid levels (0 = no multi-grid)
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MGLEVEL= 3
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%
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% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
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MGCYCLE= W_CYCLE
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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% Convective numerical method (JST, JST_KE, JST_MAT, LAX-FRIEDRICH, CUSP, ROE, AUSM,
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% AUSMPLUSUP, AUSMPLUSUP2, AUSMPWPLUS, HLLC, TURKEL_PREC,
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% SW, MSW, FDS, SLAU, SLAU2, L2ROE, LMROE)
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CONV_NUM_METHOD_FLOW= JST
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%
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% Max number of iterations of the linear solver for the implicit formulation
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LINEAR_SOLVER_ITER= 20
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%
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% ------------------------- SCREEN/HISTORY VOLUME OUTPUT --------------------------%
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%
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% Screen output fields (use 'SU2_CFD -d <config_file>' to view list of available fields)
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SCREEN_OUTPUT= (TIME_ITER, INNER_ITER, RMS_DENSITY, LIFT, MOMENT_Z)
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%
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% History output groups (use 'SU2_CFD -d <config_file>' to view list of available fields)
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HISTORY_OUTPUT= (ITER, RMS_RES, AERO_COEFF, CAUCHY, WALL_TIME)
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%
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% ------------------------- INPUT/OUTPUT FILE INFORMATION --------------------------%
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%
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% Mesh input file
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MESH_FILENAME= mesh_NACA0012_inv.su2
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%
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% Mesh input file format (SU2, CGNS)
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MESH_FORMAT= SU2
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%
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% Restart flow input file
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SOLUTION_FILENAME= restart_gust.dat
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RESTART_FILENAME= restart_gust.dat
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SURFACE_FILENAME= surface_gust
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VOLUME_FILENAME= volume_gust
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CONV_FILENAME= history_gust
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%
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% Output tabular file format (TECPLOT, CSV)
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TABULAR_FORMAT= CSV
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%
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% Files to output
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% Possible formats : (TECPLOT, TECPLOT_BINARY, SURFACE_TECPLOT,
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% SURFACE_TECPLOT_BINARY, CSV, SURFACE_CSV, PARAVIEW, PARAVIEW_BINARY, SURFACE_PARAVIEW,
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% SURFACE_PARAVIEW_BINARY, MESH, RESTART_BINARY, RESTART_ASCII, CGNS, SURFACE_CGNS, STL)
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OUTPUT_FILES= (TECPLOT, SURFACE_TECPLOT)
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‎TestCases/hybrid_regression.py‎

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cosine_gust.test_vals = [-2.418813, 0.004650, -0.001878, -0.000637, -0.000271]
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cosine_gust.unsteady = True
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test_list.append(cosine_gust)
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# Gust with mesh deformation
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gust_mesh_defo = TestCase('gust_with_mesh_deformation')
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gust_mesh_defo.cfg_dir = "gust"
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gust_mesh_defo.cfg_file = "gust_with_mesh_deformation.cfg"
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gust_mesh_defo.test_iter = 25
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gust_mesh_defo.test_vals = [-1.585670, 0.004771, 0.000413]
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gust_mesh_defo.unsteady = True
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test_list.append(gust_mesh_defo)
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# Aeroelastic
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aeroelastic = TestCase('aeroelastic')

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