From 31238be0c84fb7c983b3b3634c6f8e2a0fa137f8 Mon Sep 17 00:00:00 2001
From: Paul Dechamps <paul.dechamps@uliege.be>
Date: Mon, 27 Jan 2025 19:19:37 +0100
Subject: [PATCH] (feat) Refactor optimzation problem setup
---
blast/api/mda_api.py | 109 ++++++++++++++++++-
blast/mdao/opti_NACA2.py | 196 ++++++++++++++++++++++++++++++++++
blast/mdao/opti_transonic.py | 2 +-
blast/mdao/opti_transonic2.py | 179 +++++++++++++++++++++++++++++++
4 files changed, 483 insertions(+), 3 deletions(-)
create mode 100644 blast/mdao/opti_NACA2.py
create mode 100644 blast/mdao/opti_transonic2.py
diff --git a/blast/api/mda_api.py b/blast/api/mda_api.py
index 55b5bab..dbff35b 100644
--- a/blast/api/mda_api.py
+++ b/blast/api/mda_api.py
@@ -24,7 +24,6 @@ from fwk.coloring import ccolors
import openmdao.api as om
import blast
import blast.blUtils as vutils
-from pygeo import DVGeometryCST
from scipy.optimize import least_squares
import fwk
@@ -79,7 +78,7 @@ class BlasterSolver(om.ExplicitComponent):
self.coupler.run(write=False)
self.__write(sfx='baseline')
self.coupler.reset()
- print('object created')
+ print('BLASTER objects created')
def setup(self):
self.add_input('aoa', val=0.0, desc='Flow angle of attack')
@@ -205,6 +204,7 @@ class BlasterSolver(om.ExplicitComponent):
def getBoundaryFFDGeometry(self):
"""Airfoil FFD geometry
"""
+ from pygeo import DVGeometryCST
with open('surface_DVGeo.dat', 'w') as f:
for i, node_coord in enumerate(self.isol.vBnd[0][0].nodesCoord):
f.write(f"{node_coord[0]} {node_coord[1]}\n")
@@ -498,3 +498,108 @@ class BlasterFFDGeometry(om.ExplicitComponent):
Ri = calc_R(*center)
R = Ri.mean()
return center, R
+
+class groupMDA(om.Group):
+ def __init__(self, icfg, vcfg, ocfg):
+ super().__init__()
+ self.icfg = icfg
+ self.vcfg = vcfg
+ self.ocfg = ocfg
+
+ if 'aoa' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for aoa is missing')
+ if self.ocfg['geometryType'] == 'NACA':
+ if 'tau' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for tau is missing')
+ if 'eps' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for eps is missing')
+ if 'p' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for p is missing')
+ for key in self.ocfg['initialValues']:
+ if key not in ['aoa', 'tau', 'eps', 'p']:
+ raise KeyError('Invalid key in initialValues', key)
+ elif self.ocfg['geometryType'] == 'FFD':
+ if 'upper_shape' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for upper_shape is missing')
+ if 'lower_shape' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for lower_shape is missing')
+ if 'class_shape_n1' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for class_shape_n1 is missing')
+ if 'class_shape_n2' not in self.ocfg['initialValues']:
+ raise ValueError('Initial value for class_shape_n2 is missing')
+ for key in self.ocfg['initialValues']:
+ if key not in ['aoa', 'upper_shape', 'lower_shape', 'class_shape_n1', 'class_shape_n2']:
+ raise KeyError('Invalid key in initialValues', key)
+
+ def setup(self):
+ # Add the MDAO components
+ blaster = BlasterSolver(self.vcfg, self.icfg)
+
+ print('Optimization setup')
+ print('------------------')
+ # Design variables box
+ self.add_subsystem('dvs', om.IndepVarComp(), promotes=['*'])
+ self.add_subsystem('mod', BlasterModeUpdater(tolerance=10., force_mode=self.ocfg['mode'])) # Mode updater
+ self.add_subsystem('mesh', blaster.getBoundaryMesh())
+ # Geometry component
+ if self.ocfg['geometryType'] == 'NACA':
+ print('Adding NACA geometry')
+ self.add_subsystem('geometry', blaster.getBoundaryNACAGeometry())
+ elif self.ocfg['geometryType'] == 'FFD':
+ print('Adding FFD geometry')
+ self.add_subsystem('geometry', blaster.getBoundaryFFDGeometry())
+ # Add an intermediate variable for the constraint (such that upper_shape[0] = lower_shape[0])
+ self.add_subsystem('constraint_comp', om.ExecComp('constraint_var = lower_shape[0] + upper_shape[0]',
+ lower_shape=np.zeros(len(self.ocfg['initialValues']['upper_shape']['value'])), upper_shape=np.zeros(len(self.ocfg['initialValues']['lower_shape']['value']))), promotes=['*'])
+ else:
+ raise ValueError('Invalid geometryType', self.ocfg['geometryType'])
+ # Solver
+ self.add_subsystem('solver', blaster)
+ # Objectives
+ for obj in self.ocfg['objectives']:
+ print('Adding objective', obj['name'])
+ self.add_subsystem('obj_cmp_'+obj['name'], obj['object'], promotes=obj['promotions'])
+
+ # Connect meshes
+ self.connect('mesh.x_aero0', 'geometry.x_aero0')
+ self.connect('geometry.x_aero_out', 'solver.x_aero')
+ self.connect('mod.visc_mode', 'solver.visc_mode')
+
+ if 'nonlinear_solver' in self.ocfg:
+ self.nonlinear_solver = self.ocfg['nonlinearSolver']
+ if 'linear_solver' in self.ocfg:
+ self.linear_solver = self.ocfg['linearSolver']
+ print('')
+
+ def configure(self):
+ print('Optimization config')
+ print('------------------')
+ for variable, setup in self.ocfg['initialValues'].items():
+ print(f'- dvs output {variable} linked to {setup["link"]} with value {setup["value"]}')
+ self.dvs.add_output(variable, val=setup['value'])
+ self.connect(variable, setup['link']+'.'+variable)
+ if variable in self.ocfg['designVariables']:
+ design_config = self.ocfg['designVariables'][variable]
+ print(f'- design variable {variable} with bounds {design_config["lower_bound"]} {design_config["upper_bound"]} and scaler {design_config["scaler"]}')
+ self.add_design_var(variable, lower=design_config['lower_bound'], upper=design_config['upper_bound'], scaler=design_config['scaler'])
+
+ for const in self.ocfg['constraints']:
+ if const['type'] == 'equality':
+ print('- equality constraint:', const['name'], '=', const['value'])
+ self.add_constraint(const['name'], equals=const['value'], scaler=const['scaler'])
+ elif const['type'] == 'inequality':
+ print('- inequality constraint:', const['name'], end=' ')
+ if 'lower' in const:
+ print('-- lower bound:', const['lower'])
+ self.add_constraint(const['name'], lower=const['lower'], scaler=const['scaler'])
+ elif 'upper' in const:
+ print('-- upper bound:', const['upper'])
+ self.add_constraint(const['name'], upper=const['upper'], scaler=const['scaler'])
+ if self.ocfg['geometryType'] == 'FFD':
+ self.add_constraint('constraint_var', equals=0.0, linear=True)
+
+ for obj in self.ocfg['objectives']:
+ print('- objective:', obj['name'], 'linked to', obj['link'])
+ self.connect(obj['link']+'.'+obj['name'], obj['name'])
+ self.add_objective('obj', scaler=obj['scaler'])
+ print('')
diff --git a/blast/mdao/opti_NACA2.py b/blast/mdao/opti_NACA2.py
new file mode 100644
index 0000000..8666f19
--- /dev/null
+++ b/blast/mdao/opti_NACA2.py
@@ -0,0 +1,196 @@
+#!/usr/bin/env python3
+# -*- coding: utf-8 -*-
+
+# Copyright 2024 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 2024
+# Optimization case using NACA parametrization
+
+from fwk.wutils import parseargs
+import fwk
+from fwk.testing import *
+from fwk.coloring import ccolors
+
+from blast.api.mda_api import groupMDA
+
+import numpy as np
+import openmdao.api as om
+
+def cfgInviscid(nthrds, verb):
+ import os.path
+ # Parameters
+ return {
+ # Options
+ 'scenario' : 'aerodynamic',
+ 'task' : 'optimization',
+ 'Threads' : nthrds, # number of threads
+ 'Verb' : verb, # verbosity
+ # Model (geometry or mesh)
+ 'File' : os.path.dirname(os.path.dirname(os.path.abspath(__file__))) + '/models/dart/n0012.geo', # Input file containing the model
+ 'Pars' : {'xLgt' : 50, 'yLgt' : 50, 'msF' : 30, 'msTe' : 0.01, 'msLe' : 0.0075}, # 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
+ 'dbc' : False,
+ 'Upstream' : 'upstream',
+ # Freestream
+ 'M_inf' : 0.1, # freestream Mach number
+ 'AoA' : 0., # 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
+ 'Minf' : 0.1, # Freestream Mach number (used for the computation of the time step only)
+ 'CFL0' : 1., # Inital CFL number of the calculation
+ 'Verb': verb, # Verbosity level of the solver
+ 'couplIter': 50, # Maximum number of iterations
+ 'couplTol' : 1e-3, # Tolerance of the VII methodology
+ 'iterPrint': 5, # int, number of iterations between outputs
+ 'resetInv' : True, # bool, flag to reset the inviscid calculation at every iteration.
+ 'sections' : [0], # List of sections for boundary layer calculation
+ 'xtrF' : [0.05, 0.05], # Forced transition location
+ 'interpolator' : 'Matching',# Interpolator for the coupling
+ 'nSections' : 1, # Number of sections in the domain
+ 'span' : 1.0 # Wing span
+ }
+
+def cfgOpti():
+ return{
+ 'geometryType': 'NACA',
+ 'mode': 'visc',
+ 'linearSolver': om.DirectSolver(),
+ 'objectives': [{'name': 'cd',
+ 'link': 'solver',
+ 'object': om.ExecComp('obj = cd'),
+ 'promotions': ['obj', 'cd'],
+ 'scaler': 1000}
+ ],
+ 'initialValues': {'aoa':{'link':'solver', 'value': 0.0},
+ 'tau':{'link':'geometry', 'value': 0.12},
+ 'eps':{'link':'geometry', 'value': 0.0},
+ 'p':{'link': 'geometry', 'value': 0.4}
+ },
+ 'designVariables': {'aoa':{'lower_bound': -3.0, 'upper_bound': 3.0, 'scaler': 1},
+ 'eps':{'lower_bound': 0.0, 'upper_bound': 0.05, 'scaler': 10},
+ 'p':{'lower_bound': 0.35, 'upper_bound': 0.45, 'scaler': 10}
+ },
+ 'constraints': [{'name': 'solver.cl', 'type': 'equality', 'value': 0.4, 'scaler': 10}]
+ }
+
+def main():
+ # Timer.
+ tms = fwk.Timers()
+ tms['total'].start()
+
+ args = parseargs()
+ icfg = cfgInviscid(args.k, args.verb)
+ vcfg = cfgBlast(args.verb)
+ ocfg = cfgOpti()
+
+ prob = om.Problem()
+ prob.model = groupMDA(icfg, vcfg, ocfg)
+
+ prob.driver = om.ScipyOptimizeDriver()
+ prob.driver.options['optimizer'] = 'SLSQP'
+ prob.driver.options['tol'] = 1e-3
+
+ recorder = om.SqliteRecorder('reports/BlasterSolver_file.sql')
+
+ prob.driver.add_recorder(recorder)
+ prob.driver.recording_options['record_objectives'] = True
+ prob.driver.recording_options['record_desvars'] = True
+ prob.driver.recording_options['includes'] = ['aoa', 'solver.cl', 'solver.cd', 'mesh.x_aero0', 'geometry.x_aero_out']
+
+ prob.setup()
+ #prob.check_partials(includes=['cl', 'aoa'], compact_print=True)
+ prob.run_driver()
+
+ # Instantiate your CaseReader
+ cr = om.CaseReader(prob.get_reports_dir() / "../BlasterSolver_file.sql")
+ # Isolate "problem" as your source
+ driver_cases = cr.list_cases('driver', out_stream=None)
+
+ # Get evolution of f and x
+ aoa_evol = []
+ cl_evol = []
+ cd_evol = []
+ shape = []
+ shape0 = []
+
+ for c in driver_cases:
+ case = cr.get_case(c)
+ aoa_evol.append(case.get_val('aoa')[0]*180/np.pi)
+ cl_evol.append(case.get_val('solver.cl')[0])
+ cd_evol.append(case.get_val('solver.cd')[0])
+ shape0.append(case.get_val('mesh.x_aero0'))
+ shape.append(case.get_val('geometry.x_aero_out'))
+
+ print('success')
+ print('aoa:', prob['aoa']*np.pi/180)
+ print('cl:', prob['solver.cl'])
+ print('cd:', prob['solver.cd'])
+ print('obj:', prob['obj'])
+
+ # Recover selig format
+ shape0_selig = np.array(shape0[0])
+ shape1_selig = np.array(shape[-1])
+ for i, val in enumerate(prob.model.solver.isol.vBnd[0][0].connectListNodes):
+ for j in range(prob.model.solver.isol.getnDim()):
+ shape0_selig[i*prob.model.solver.isol.getnDim()+j] = shape0[0][val*prob.model.solver.isol.getnDim()+j]
+ shape1_selig[i*prob.model.solver.isol.getnDim()+j] = shape[-1][val*prob.model.solver.isol.getnDim()+j]
+ from matplotlib import pyplot as plt
+
+ plt.plot(shape0_selig[0::2], shape0_selig[1::2], '--', color='grey', label='Initial shape - cl = {:.2f} - cd = {:.5f}'.format(cl_evol[0], cd_evol[0]))
+ plt.plot(shape1_selig[0::2], shape1_selig[1::2], '-', color='blue', label='Final shape - cl = {:.2f} - cd = {:.5f}'.format(cl_evol[-1], cd_evol[-1]))
+ plt.legend()
+ plt.axis('equal')
+ plt.show()
+ quit()
+
+
+
+ plt.plot(shape0[0][::2], shape0[0][1::2], 'x', color='grey')
+ for xx in shape:
+ plt.plot(xx[::2], xx[1::2], 'x', color='blue')
+ plt.axis('equal')
+ plt.show()
+ quit()
+
+
+if __name__ == "__main__":
+ main()
diff --git a/blast/mdao/opti_transonic.py b/blast/mdao/opti_transonic.py
index 7ca7ffe..7b74ed3 100644
--- a/blast/mdao/opti_transonic.py
+++ b/blast/mdao/opti_transonic.py
@@ -63,7 +63,7 @@ def cfgInviscid(nthrds, verb):
'y_ref' : 0.0, # reference point for moment computation (y)
'z_ref' : 0.0, # reference point for moment computation (z)
# Numerical
- 'LSolver' : 'SparseLu', # inner solver (Pardiso, MUMPS or GMRES)
+ 'LSolver' : 'SparseLU', # 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
diff --git a/blast/mdao/opti_transonic2.py b/blast/mdao/opti_transonic2.py
new file mode 100644
index 0000000..68c695f
--- /dev/null
+++ b/blast/mdao/opti_transonic2.py
@@ -0,0 +1,179 @@
+#!/usr/bin/env python3
+# -*- coding: utf-8 -*-
+
+# Copyright 2024 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 2024
+# Optimization for a transonic case
+
+from fwk.wutils import parseargs
+import fwk
+from fwk.testing import *
+from fwk.coloring import ccolors
+
+from blast.api.mda_api import groupMDA
+
+import numpy as np
+import openmdao.api as om
+
+def cfgInviscid(nthrds, verb):
+ import os.path
+ # Parameters
+ return {
+ # Options
+ 'scenario' : 'aerodynamic',
+ 'task' : 'optimization',
+ 'Threads' : nthrds, # number of threads
+ 'Verb' : verb, # verbosity
+ # Model (geometry or mesh)
+ 'File' : os.path.dirname(os.path.dirname(os.path.abspath(__file__))) + '/models/dart/n0012.geo', # Input file containing the model
+ 'Pars' : {'xLgt' : 50, 'yLgt' : 50, 'msF' : 20, 'msTe' : 0.01, 'msLe' : 0.008}, # 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' : 0.78, # freestream Mach number
+ 'AoA' : 0., # 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' : 'SparseLU', # 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' : 50 # solver maximum number of iterations
+ }
+
+def cfgBlast(verb):
+ return {
+ 'Re' : 1e8, # Freestream Reynolds number
+ 'Minf' : 0.78, # Freestream Mach number (used for the computation of the time step only)
+ 'CFL0' : 1., # Inital CFL number of the calculation
+ 'Verb': verb, # Verbosity level of the solver
+ 'couplIter': 75, # Maximum number of iterations
+ 'couplTol' : 1e-4, # Tolerance of the VII methodology
+ 'iterPrint': 5, # int, number of iterations between outputs
+ 'resetInv' : True, # bool, flag to reset the inviscid calculation at every iteration.
+ 'sections' : [0], # List of sections for boundary layer calculation
+ 'xtrF' : [0.05, 0.05], # Forced transition location
+ 'interpolator' : 'Matching',# Interpolator for the coupling
+ 'nSections' : 1, # Number of sections in the domain
+ 'span' : 1.0 # Wing span
+ }
+
+def cfgOpti():
+ return{
+ 'geometryType': 'FFD',
+ 'mode': 'visc',
+ 'linearSolver': om.DirectSolver(),
+ 'objectives': [{'name': 'cd',
+ 'link': 'solver',
+ 'object': om.ExecComp('obj = cd'),
+ 'promotions': ['obj', 'cd'],
+ 'scaler': 1000}
+ ],
+ 'initialValues': {'aoa':{'link':'solver', 'value': 0.0},
+ 'upper_shape':{'link':'geometry', 'value': [0.17553542, 0.14723497, 0.14531762, 0.13826955]},
+ 'lower_shape':{'link':'geometry', 'value': [-0.16935506, -0.15405552, -0.13912672, -0.14168947]},
+ 'class_shape_n1':{'link': 'geometry', 'value': 0.5},
+ 'class_shape_n2':{'link': 'geometry', 'value': 1.0}
+ },
+ 'designVariables': {'aoa':{'lower_bound': -5.0, 'upper_bound': 5.0, 'scaler': 1.0},
+ 'upper_shape':{'lower_bound': -0.15, 'upper_bound': 0.25, 'scaler': 10},
+ 'lower_shape':{'lower_bound': -0.2, 'upper_bound': 0.2, 'scaler': 10}
+ },
+ 'constraints': [{'name': 'solver.cl', 'type': 'equality', 'value': 0.4, 'scaler': 10, 'linear': False},
+ {'name': 'geometry.thickness', 'type': 'inequality', 'lower': 0.12, 'scaler':10, 'upper':None, 'linear': True},
+ {'name': 'geometry.LEradius', 'type': 'equality', 'value': 0.0224, 'scaler':100, 'linear': True}]
+ }
+
+def main():
+ # Timer.
+ tms = fwk.Timers()
+ tms['total'].start()
+
+ args = parseargs()
+ icfg = cfgInviscid(args.k, args.verb)
+ vcfg = cfgBlast(args.verb)
+ ocfg = cfgOpti()
+
+ prob = om.Problem()
+ prob.model = groupMDA(icfg, vcfg, ocfg)
+
+ prob.driver = om.ScipyOptimizeDriver()
+ prob.driver.options['optimizer'] = 'SLSQP'
+ prob.driver.options['tol'] = 1e-4
+
+ recorder = om.SqliteRecorder('reports/BlasterSolver_file.sql')
+
+ prob.driver.add_recorder(recorder)
+ prob.driver.recording_options['record_objectives'] = True
+ prob.driver.recording_options['record_desvars'] = True
+ prob.driver.recording_options['includes'] = ['aoa', 'solver.cl', 'solver.cd', 'mesh.x_aero0', 'geometry.x_aero_out']
+
+ prob.setup()
+ # print('check')
+ # prob.check_partials(includes=['cl', 'cd'], compact_print=True)
+ # print('done')
+ prob.run_driver()
+
+ # problem timers
+ print(prob.model.solver.tms)
+
+ # Case reader
+ cr = om.CaseReader(prob.get_reports_dir() / "../BlasterSolver_file.sql")
+ driver_cases = cr.list_cases('driver', out_stream=None)
+
+ # Get evolution of f and x
+ aoa_evol = []
+ cl_evol = []
+ cd_evol = []
+ shape = []
+ shape0 = []
+
+ for c in driver_cases:
+ case = cr.get_case(c)
+ aoa_evol.append(case.get_val('aoa')[0])
+ cl_evol.append(case.get_val('solver.cl')[0])
+ cd_evol.append(case.get_val('solver.cd')[0])
+ shape0.append(case.get_val('mesh.x_aero0'))
+ shape.append(case.get_val('geometry.x_aero_out'))
+
+ print('aoa:', prob['aoa'])
+ print('cl:', prob['solver.cl'])
+ print('cd:', prob['solver.cd'])
+ print('obj:', prob['obj'])
+
+ # eof
+ tms['total'].stop()
+ print(tms)
+
+if __name__ == "__main__":
+ main()
--
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