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Add LINELET regression case for laminar NACA0012 #2899

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Add LINELET regression case for laminar NACA0012 #2899

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98 changes: 98 additions & 0 deletions TestCases/navierstokes/naca0012/lam_NACA0012_LINELET.cfg
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: NACA0012 Laminar (Re 5000), LINELET preconditioner %
% Author: Francisco Palacios %
% Institution: Stanford University %
% Date: Sep 28, 2012 %
% File Version 8.5.0 "Harrier" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= NAVIER_STOKES
KIND_TURB_MODEL= NONE
MATH_PROBLEM= DIRECT
RESTART_SOL= NO

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
MACH_NUMBER= 0.5
AOA= 1.0
FREESTREAM_TEMPERATURE= 288.15
REYNOLDS_NUMBER= 5000.0
REYNOLDS_LENGTH= 1.0

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
REF_LENGTH= 1.0
REF_AREA= 1.0

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
MARKER_HEATFLUX= ( airfoil, 0.0 )
MARKER_FAR= ( farfield )
MARKER_PLOTTING= ( airfoil )
MARKER_MONITORING= ( airfoil )

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
CFL_NUMBER= 30.0
CFL_ADAPT= NO
CFL_ADAPT_PARAM= ( 0.5, 1.5, 1.0, 100.0 )
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
ITER= 10000
LINEAR_SOLVER= FGMRES
LINEAR_SOLVER_ERROR= 1E-1
LINEAR_SOLVER_ITER= 3

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
MGLEVEL= 3
MGCYCLE= V_CYCLE
MG_PRE_SMOOTH= ( 4, 4, 4, 4 )
MG_POST_SMOOTH= ( 4, 4, 4, 4 )
MG_CORRECTION_SMOOTH= ( 1, 1, 1, 1 )
MG_DAMP_RESTRICTION= 0.5
MG_DAMP_PROLONGATION= 0.5

% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
CONV_NUM_METHOD_FLOW= ROE
MUSCL_FLOW= YES
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
VENKAT_LIMITER_COEFF= 0.0001
JST_SENSOR_COEFF= ( 0.5, 0.02 )
TIME_DISCRE_FLOW= EULER_IMPLICIT

% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
CONV_RESIDUAL_MINVAL= -12
CONV_STARTITER= 10
CONV_CAUCHY_ELEMS= 100
CONV_CAUCHY_EPS= 1E-10

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
MESH_FILENAME= mesh_NACA0012_lam_hybrid_v1.su2
MESH_FORMAT= SU2
MESH_OUT_FILENAME= mesh_out
SOLUTION_FILENAME= solution_flow
SOLUTION_ADJ_FILENAME= solution_adj
TABULAR_FORMAT= CSV
CONV_FILENAME= history
RESTART_FILENAME= restart_flow
RESTART_ADJ_FILENAME= restart_adj
VOLUME_FILENAME= flow
VOLUME_ADJ_FILENAME= adjoint
GRAD_OBJFUNC_FILENAME= of_grad
SURFACE_FILENAME= surface_flow
SURFACE_ADJ_FILENAME= surface_adjoint
OUTPUT_WRT_FREQ= 250

LINEAR_SOLVER_PREC= LINELET
8 changes: 8 additions & 0 deletions TestCases/serial_regression.py
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Expand Up @@ -195,6 +195,14 @@ def main():
cylinder_lowmach.test_vals = [-6.453096, -0.991328, 0.722165, 66.048089, 0.000000]
test_list.append(cylinder_lowmach)

# Laminar NACA0012 with linelet preconditioner (see #2877)
lam_naca0012_linelet = TestCase('lam_naca0012_linelet')
lam_naca0012_linelet.cfg_dir = "navierstokes/naca0012"
lam_naca0012_linelet.cfg_file = "lam_NACA0012_LINELET.cfg"
lam_naca0012_linelet.test_iter = 20
lam_naca0012_linelet.test_vals = [-5.282867, -2.845208, -2.852421, 0.154542]
test_list.append(lam_naca0012_linelet)

# 2D Poiseuille flow (body force driven with periodic inlet / outlet)
poiseuille = TestCase('poiseuille')
poiseuille.cfg_dir = "navierstokes/poiseuille"
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