(feat) Modify solver interface for new data structures and new restart capability

blast/tests/t_restart_2D.py

+#!/usr/bin/env python3
+# -*- coding: utf-8 -*-
+
+# Copyright 2022 University of Liège
+#
+# Licensed under the Apache License, Version 2.0 (the "License");
+# you may not use this file except in compliance with the License.
+# You may obtain a copy of the License at
+#
+#     http://www.apache.org/licenses/LICENSE-2.0
+#
+# Unless required by applicable law or agreed to in writing, software
+# distributed under the License is distributed on an "AS IS" BASIS,
+# WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+# See the License for the specific language governing permissions and
+# limitations under the License.
+
+
+# @author Paul Dechamps
+# @date 2025
+# Test the restart file
+
+# Imports.
+
+import blast.blUtils as vutils
+import numpy as np
+
+from fwk.wutils import parseargs
+import fwk
+from fwk.testing import *
+from fwk.coloring import ccolors
+
+import math
+
+def cfgInviscid(nthrds, verb):
+    import os.path
+    # Parameters
+    return {
+    # Options
+    'scenario' : 'aerodynamic',
+    'task' : 'analysis',
+    'Threads' : nthrds, # number of threads
+    'Verb' : verb, # verbosity
+    # Model (geometry or mesh)
+    'File' : os.path.dirname(os.path.abspath(__file__)) + '/../models/dart/n0012.geo', # Input file containing the model
+    'Pars' : {'xLgt' : 50, 'yLgt' : 50, 'growthRatio': 1.3, 'msTe' : 0.01, 'msLe' : 0.01}, # parameters for input file model
+    'Dim' : 2, # problem dimension
+    'Format' : 'gmsh', # save format (vtk or gmsh)
+    # Markers
+    'Fluid' : 'field', # name of physical group containing the fluid
+    'Farfield' : ['upstream', 'farfield', 'downstream'], # LIST of names of physical groups containing the farfield boundaries (upstream/downstream should be first/last element)
+    'Wing' : 'airfoil', # LIST of names of physical groups containing the lifting surface boundary
+    'Wake' : 'wake', # LIST of names of physical group containing the wake
+    'WakeTip' : 'wakeTip', # LIST of names of physical group containing the edge of the wake
+    'Te' : 'te', # LIST of names of physical group containing the trailing edge
+    'Upstream' : 'upstream',
+    # Freestream
+    'M_inf' : 0.2, # freestream Mach number
+    'AoA' : 1., # freestream angle of attack
+    # Geometry
+    'S_ref' : 1., # reference surface length
+    'c_ref' : 1., # reference chord length
+    'x_ref' : .25, # reference point for moment computation (x)
+    'y_ref' : 0.0, # reference point for moment computation (y)
+    'z_ref' : 0.0, # reference point for moment computation (z)
+    # Numerical
+    'LSolver' : 'GMRES', # inner solver (Pardiso, MUMPS or GMRES)
+    'G_fill' : 2, # fill-in factor for GMRES preconditioner
+    'G_tol' : 1e-5, # tolerance for GMRES
+    'G_restart' : 50, # restart for GMRES
+    'Rel_tol' : 1e-6, # relative tolerance on solver residual
+    'Abs_tol' : 1e-8, # absolute tolerance on solver residual
+    'Max_it' : 20 # solver maximum number of iterations
+    }
+
+def cfgBlast(verb):
+    return {
+        'Re' : 1e7,                 # Freestream Reynolds number
+        'CFL0' : 1,                 # Inital CFL number of the calculation
+        'couplIter': 50,            # Maximum number of iterations
+        'couplTol' : 1e-4,          # Tolerance of the VII methodology
+        'iterPrint': 1,             # int, number of iterations between outputs
+        'resetInv' : True,          # bool, flag to reset the inviscid calculation at every iteration.
+        'xtrF' : [None, 0.4],       # Forced transition locations
+        'interpolator' : 'Matching',# Interpolator for the coupling
+        
+        # Restart file
+        'restart_solution' : False, # Restart solution from file
+        'restart_inputName': None, # Name of the restart file to read
+        'restart_outputName': 'naca0012_restart', # Name of the restart file saved on disk
+        'iterSaveRestart' : 1, # Number of iterations between restart file save
+        'saveCouplingIters': True,
+    }
+
+def main():
+    import os.path
+
+    # Iteration to restart
+    iterRestart = 10
+    
+    # Timer.
+    tms = fwk.Timers()
+    tms['total'].start()
+
+    args = parseargs()
+    icfg = cfgInviscid(args.k, args.verb)
+    vcfg = cfgBlast(args.verb)
+
+    tms['pre'].start()
+    coupler, isol, vsol = vutils.initBlast(icfg, vcfg)
+    tms['pre'].stop()
+
+    print(ccolors.ANSI_BLUE + 'PySolving...' + ccolors.ANSI_RESET)
+    tms['solver'].start()
+    aeroCoeffs_ref = coupler.run()
+    tms['solver'].stop()
+
+    del isol, vsol, coupler
+
+    vcfg["restart_solution"] = True
+    vcfg["restart_inputName"] = os.path.dirname(os.path.dirname(os.path.dirname(os.path.abspath(__file__))))\
+                                + '/workspace/blast_tests_t_restart/'\
+                                + vcfg["restart_outputName"] + f"_{iterRestart}"
+    vcfg["iterSaveRestart"] = float('inf')
+
+
+    coupler, isol, vsol = vutils.initBlast(icfg, vcfg)
+    aeroCoeff_restart = coupler.run()
+
+    # Save in vtk format
+    vutils.save(vsol.bodies[0].sections)
+
+    # Display results.
+    print(ccolors.ANSI_BLUE + 'PyRes...' + ccolors.ANSI_RESET)
+    print('      Re        M    alpha       Cl       Cd      Cdp      Cdf       Cm')
+    print('{0:6.1f}e6 {1:8.2f} {2:8.1f} {3:8.4f} {4:8.4f} {5:8.4f} {6:8.4f} {7:8.4f}'.format(vcfg['Re']/1e6, isol.getMinf(), isol.getAoA()*180/math.pi, isol.getCl(), vsol.Cdt, vsol.Cdp, vsol.Cdf, isol.getCm()))
+    print('')
+    total_iters_ref = len(aeroCoeffs_ref['Cl'])
+    total_iters_restart = len(aeroCoeff_restart['Cl'])
+    print(f"Number of iterations without restart: {total_iters_ref}")
+    print(f'Restarted at iteration {iterRestart}')
+    print(f"Number of iterations with restart: {total_iters_restart}")
+    tms['total'].stop()
+
+    print(ccolors.ANSI_BLUE + 'PyTiming...' + ccolors.ANSI_RESET)
+    print('CPU statistics')
+    print(tms)
+    print('SOLVERS statistics')
+    print(coupler.tms)
+
+    bl_solution = vutils.getSolution(vsol.bodies[0].sections, write=False)[0]
+
+    final_res_ref = np.log10((aeroCoeffs_ref['Cd'][-1] - aeroCoeffs_ref['Cd'][-2]) / aeroCoeffs_ref['Cd'][-1])
+    final_res_restart = np.log10((aeroCoeff_restart['Cd'][-1] - aeroCoeff_restart['Cd'][-2]) / aeroCoeff_restart['Cd'][-1])
+    
+    # Test solution
+    print(ccolors.ANSI_BLUE + 'PyTesting...' + ccolors.ANSI_RESET)
+    tests = CTests()
+    tests.add(CTest('Cl compare', aeroCoeff_restart['Cl'][-1], aeroCoeffs_ref['Cl'][-1], 1e-8))
+    tests.add(CTest('Cd compare', aeroCoeff_restart['Cd'][-1], aeroCoeffs_ref['Cd'][-1], 1e-8))
+    tests.add(CTest('nIters', total_iters_restart, total_iters_ref-iterRestart-1, 0, forceabs=True))
+    tests.add(CTest('Final residual Cd (log)', final_res_restart, final_res_ref, 1e-6))
+    tests.run()
+    # eof
+    print('')
+
+if __name__ == "__main__":
+    main()