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Documentation + test case RAMP_MUSCL
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‎TestCases/euler/naca0012/inv_NACA0012_Roe_MUSCL_ramp.cfg‎

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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% %
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% SU2 configuration file %
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% Case description: Transonic inviscid flow around a NACA0012 (regression) %
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% Author: Thomas D. Economon %
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% Institution: Stanford University %
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% Date: 2012.10.07 %
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% File Version 8.3.0 "Harrier" %
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% %
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
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% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
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%
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SOLVER= EULER
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MATH_PROBLEM= DIRECT
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RESTART_SOL= NO
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% ----------- COMPRESSIBLE AND INCOMPRESSIBLE FREE-STREAM DEFINITION ----------%
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%
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MACH_NUMBER= 0.8
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AOA= 1.25
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FREESTREAM_PRESSURE= 101325.0
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FREESTREAM_TEMPERATURE= 288.15
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% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
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%
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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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REF_LENGTH= 1.0
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REF_AREA= 1.0
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REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE
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% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
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%
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MARKER_EULER= ( airfoil )
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MARKER_FAR= ( farfield )
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MARKER_PLOTTING= ( airfoil )
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MARKER_MONITORING= ( airfoil )
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% ------------- COMMON PARAMETERS TO DEFINE THE NUMERICAL METHOD --------------%
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%
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NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
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CFL_NUMBER= 20.0
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CFL_ADAPT= NO
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CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
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RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
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ITER= 1000
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LINEAR_SOLVER= BCGSTAB
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LINEAR_SOLVER_ERROR= 1E-6
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LINEAR_SOLVER_ITER= 5
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% -------------------------- MULTIGRID PARAMETERS -----------------------------%
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%
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MGLEVEL= 3
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MGCYCLE= W_CYCLE
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MG_PRE_SMOOTH= ( 1, 2, 2, 2 )
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MG_POST_SMOOTH= ( 1, 1, 1, 1 )
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MG_CORRECTION_SMOOTH= ( 1, 1, 1, 1 )
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MG_DAMP_RESTRICTION= 0.80
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MG_DAMP_PROLONGATION= 0.80
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% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
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%
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CONV_NUM_METHOD_FLOW= ROE
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MUSCL_FLOW= YES
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RAMP_MUSCL= YES
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RAMP_MUSCL_COEFF= (0.0, 1.0, 20.0)
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RAMP_MUSCL_POWER = 1
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KIND_MUSCL_RAMP= ITERATION
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SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
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VENKAT_LIMITER_COEFF= 0.01
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JST_SENSOR_COEFF= ( 0.5, 0.02 )
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TIME_DISCRE_FLOW= EULER_IMPLICIT
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% --------------------------- CONVERGENCE PARAMETERS --------------------------%
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%
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CONV_RESIDUAL_MINVAL= -10
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CONV_STARTITER= 10
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CONV_CAUCHY_ELEMS= 100
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CONV_CAUCHY_EPS= 1E-6
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% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
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%
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MESH_FILENAME= mesh_NACA0012_inv.su2
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MESH_FORMAT= SU2
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MESH_OUT_FILENAME= mesh_out
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SOLUTION_FILENAME= solution_flow
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SOLUTION_ADJ_FILENAME= solution_adj
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TABULAR_FORMAT= CSV
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CONV_FILENAME= history
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RESTART_FILENAME= restart_flow
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RESTART_ADJ_FILENAME= restart_adj
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VOLUME_FILENAME= flow
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VOLUME_ADJ_FILENAME= adjoint
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GRAD_OBJFUNC_FILENAME= of_grad
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SURFACE_FILENAME= surface_flow
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SURFACE_ADJ_FILENAME= surface_adjoint
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SCREEN_OUTPUT = (INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG)

‎TestCases/hybrid_regression.py‎

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naca0012.test_vals = [-4.766168, -4.287699, 0.326688, 0.022661]
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test_list.append(naca0012)
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# NACA0012 w/ MUSCL ramp
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naca0012_MUSCL_ramp = TestCase('naca0012_MUSCL_ramp')
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naca0012_MUSCL_ramp.cfg_dir = "euler/naca0012"
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naca0012_MUSCL_ramp.cfg_file = "inv_NACA0012_Roe_MUSCL_ramp.cfg"
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naca0012_MUSCL_ramp.test_iter = 30
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naca0012_MUSCL_ramp.test_vals = [-4.766168, -4.287699, 0.326688, 0.022661]
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test_list.append(naca0012_MUSCL_ramp)
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# Supersonic wedge
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wedge = TestCase('wedge')
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wedge.cfg_dir = "euler/wedge"

‎TestCases/parallel_regression.py‎

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naca0012.test_vals = [-4.607257, -4.138750, 0.327682, 0.022685]
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test_list.append(naca0012)
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# NACA0012 w/ MUSCL ramp
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naca0012_MUSCL_ramp = TestCase('naca0012_MUSCL_ramp')
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naca0012_MUSCL_ramp.cfg_dir = "euler/naca0012"
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naca0012_MUSCL_ramp.cfg_file = "inv_NACA0012_Roe_MUSCL_ramp.cfg"
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naca0012_MUSCL_ramp.test_iter = 30
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naca0012_MUSCL_ramp.test_vals = [-4.766168, -4.287699, 0.326688, 0.022661]
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test_list.append(naca0012_MUSCL_ramp)
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# Supersonic wedge
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wedge = TestCase('wedge')
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wedge.cfg_dir = "euler/wedge"

‎TestCases/serial_regression.py‎

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naca0012.test_vals = [-4.766184, -4.287722, 0.326688, 0.022661]
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test_list.append(naca0012)
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# NACA0012 w/ MUSCL ramp
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naca0012_MUSCL_ramp = TestCase('naca0012_MUSCL_ramp')
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naca0012_MUSCL_ramp.cfg_dir = "euler/naca0012"
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naca0012_MUSCL_ramp.cfg_file = "inv_NACA0012_Roe_MUSCL_ramp.cfg"
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naca0012_MUSCL_ramp.test_iter = 30
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naca0012_MUSCL_ramp.test_vals = [-4.766168, -4.287699, 0.326688, 0.022661]
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test_list.append(naca0012_MUSCL_ramp)
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# Supersonic wedge
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wedge = TestCase('wedge')
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wedge.cfg_dir = "euler/wedge"

‎config_template.cfg‎

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% Required for 2nd order upwind schemes (NO, YES)
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MUSCL_FLOW= YES
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%
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% Option to ramp the MUSCL reconstruction scheme gradually from first to second order
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RAMP_MUSCL= NO
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%
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% Coefficients for the MUSCL ramp, 1st is ramp start iteration,
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% 2nd is the ramp update frequency, 3rd is the total number of iterations of the ramp
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RAMP_MUSCL_COEFF= (1000.0, 10.0, 500.0)
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%
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% Value for modifying how aggresively the ramp is applied (cannot be less than or equal to 0)
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% < 1 = Aggresive ramp up early, slower later, > 1 slow initial ramping, more aggresive towards end
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RAMP_MUSCL_POWER = 1
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%
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% Type of MUSCL ramp function used
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% ITERATION = [min(1.0, iter/endIter)]^RAMP_MUSCL_POWER
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% SMOOTH_FUNCTION = [1/2 * ( 1 - cos ( pi * min(1.0, iter/endIter)))]^RAMP_MUSCL_POWER
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KIND_MUSCL_RAMP= ITERATION
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%
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% Coefficient for blending upwind and central differences in MUSCL scheme.
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% Values range from -1 (fully one-sided) to 1 (central difference).
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MUSCL_KAPPA_FLOW= 0.0

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