def test_aerostruct_optimization_symmetry_multiple(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : True})
surf_dict = {'name' : 'wing',
'symmetry' : True,
'num_y' : 13,
'num_x' : 2,
'wing_type' : 'CRM',
'CL0' : 0.2,
'CD0' : 0.015}
OAS_prob.add_surface(surf_dict)
surf_dict.update({'name' : 'tail',
'offset':numpy.array([0., 0., 1.e7])})
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.add_desvar('wing_twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing_thickness_cp', lower=0.01, upper=0.25, scaler=1e2)
OAS_prob.add_constraint('wing_failure', upper=0.)
OAS_prob.add_desvar('tail_twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('tail_thickness_cp', lower=0.01, upper=0.25, scaler=1e2)
OAS_prob.add_constraint('tail_failure', upper=0.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('eq_con', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=1e-5)
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['fuelburn'], 1708184.640125683, places=0)
self.assertAlmostEqual(prob['wing_failure'], 1e-9)
self.assertAlmostEqual(numpy.linalg.norm(prob['wing_twist_cp']), numpy.linalg.norm(prob['tail_twist_cp']), places=3)
def test_aero_multiple_opt(self):
OAS_prob = OASProblem({'type': 'aero', 'optimize': True})
surf_dict = {
'name': 'wing',
'span': 5.,
'num_y': 3,
'span_cos_spacing': 0.
}
OAS_prob.add_surface(surf_dict)
surf_dict.update({
'name': 'tail',
'offset': numpy.array([0., 0., 10.])
})
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.add_desvar('tail.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('tail.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('tail.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('tail.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('tail_perf.CL', equals=0.5)
OAS_prob.add_objective('tail_perf.CD', scaler=1e4)
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'],
.41543435621928004,
places=5)
self.assertAlmostEqual(prob['tail_perf.CL'], .5, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'],
.0075400306289957033,
places=5)
self.assertAlmostEqual(prob['tail_perf.CD'],
.00791118243006308,
places=5)
def test_aerostruct_optimization_symmetry(self):
OAS_prob = OASProblem({'type': 'aerostruct', 'optimize': True})
surf_dict = {
'symmetry': True,
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CL0': 0.2,
'CD0': 0.015
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.add_desvar('wing.twist_cp', lower=-15., upper=15.)
OAS_prob.add_desvar('wing.thickness_cp',
lower=0.01,
upper=0.25,
scaler=1e2)
OAS_prob.add_constraint('wing_perf.failure', upper=0.)
OAS_prob.add_desvar('alpha', lower=-10., upper=10.)
OAS_prob.add_constraint('eq_con', equals=0.)
OAS_prob.add_objective('fuelburn', scaler=1e-4)
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['fuelburn'], 80248.113842385414, places=0)
self.assertAlmostEqual(prob['wing_perf.failure'], 1e-9)
def test_aero_analysis_flat_symmetry(self):
OAS_prob = OASProblem({'type': 'aero', 'optimize': False})
surf_dict = {'symmetry': True}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .45655138, places=5)
def test_struct_analysis_symmetry(self):
OAS_prob = OASProblem({'type': 'struct', 'optimize': False})
surf_dict = {'symmetry': True}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing.weight'], 83.2113646, places=3)
def test_aero_analysis_flat(self):
OAS_prob = OASProblem({'type': 'aero', 'optimize': False})
OAS_prob.add_surface({'span_cos_spacing': 0})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['wing_perf.CD'], .005524603647, places=5)
def test_aero_analysis_flat_multiple(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False})
OAS_prob.add_surface({'span_cos_spacing' : 0.})
OAS_prob.add_surface({'name' : 'tail',
'span_cos_spacing' : 0.,
'offset' : numpy.array([0., 0., 1000000.])})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['tail_CL'], .46173591841167, places=5)
def test_struct_optimization(self):
OAS_prob = OASProblem({'type' : 'struct',
'optimize' : True})
OAS_prob.add_surface()
OAS_prob.setup()
OAS_prob.add_desvar('thickness_cp', lower=0.01, upper=0.25, scaler=1e2)
OAS_prob.add_constraint('failure', upper=0.)
OAS_prob.add_objective('weight', scaler=1e-3)
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['weight'], 2010.4792274, places=2)
def test_struct_optimization_symmetry(self):
OAS_prob = OASProblem({'type' : 'struct',
'optimize' : True})
surf_dict = {'symmetry' : True}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.add_desvar('thickness_cp', lower=0.01, upper=0.25, scaler=1e2)
OAS_prob.add_constraint('failure', upper=0.)
OAS_prob.add_objective('weight', scaler=1e-3)
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['weight'], 1908.6362044761127, places=2)
def test_aerostruct_analysis(self):
OAS_prob = OASProblem({'type' : 'aerostruct',
'optimize' : False})
surf_dict = {'num_y' : 13,
'num_x' : 2,
'wing_type' : 'CRM',
'CL0' : 0.2,
'CD0' : 0.015}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['CL'], .58245256)
self.assertAlmostEqual(prob['failure'], -.431801158, places=5)
self.assertAlmostEqual(prob['fuelburn'], 1400891.8033734, places=2)
def test_aero_optimization_flat(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : True})
OAS_prob.add_surface()
OAS_prob.setup()
OAS_prob.add_desvar('twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('sweep', lower=10., upper=30.)
OAS_prob.add_desvar('dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('taper', lower=.5, upper=2.)
OAS_prob.add_constraint('CL', equals=0.5)
OAS_prob.add_objective('CD', scaler=1e4)
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['CD'], .004048702908627036, places=5)
def test_aerostruct_analysis_symmetry(self):
OAS_prob = OASProblem({'type': 'aerostruct', 'optimize': False})
surf_dict = {
'symmetry': True,
'num_y': 13,
'num_x': 2,
'wing_type': 'CRM',
'CL0': 0.2,
'CD0': 0.015
}
OAS_prob.add_surface(surf_dict)
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_perf.CL'], .58245256)
self.assertAlmostEqual(prob['wing_perf.failure'],
-.5011158763,
places=5)
self.assertAlmostEqual(prob['fuelburn'], 139970.19140120025, places=2)
def test_aero_analysis_flat_side_by_side(self):
OAS_prob = OASProblem({'type' : 'aero',
'optimize' : False})
OAS_prob.add_surface({'name' : 'wing',
'span' : 5.,
'num_y' : 3,
'span_cos_spacing' : 0.,
'offset' : numpy.array([0., -2.5, 0.])})
OAS_prob.add_surface({'name' : 'tail',
'span' : 5.,
'num_y' : 3,
'span_cos_spacing' : 0.,
'offset' : numpy.array([0., 2.5, 0.])})
OAS_prob.setup()
OAS_prob.run()
prob = OAS_prob.prob
self.assertAlmostEqual(prob['wing_CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['tail_CL'], .46173591841167, places=5)
self.assertAlmostEqual(prob['wing_CD'], .005524603647, places=5)
self.assertAlmostEqual(prob['tail_CD'], .005524603647, places=5)
# Add additional lifting surface
OAS_prob.add_surface({
'name': 'tail',
'span': 3.,
'offset': numpy.array([5., 0., 1.])
})
# Setup problem and add design variables, constraints, and objective
OAS_prob.setup()
# Set up wing variables
OAS_prob.add_desvar('wing.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('wing.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('wing.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('wing.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('wing_perf.CL', equals=0.5)
OAS_prob.add_objective('wing_perf.CD', scaler=1e4)
# Set up tail variables
OAS_prob.add_desvar('tail.twist_cp', lower=-10., upper=15.)
OAS_prob.add_desvar('tail.sweep', lower=10., upper=30.)
OAS_prob.add_desvar('tail.dihedral', lower=-10., upper=20.)
OAS_prob.add_desvar('tail.taper', lower=.5, upper=2.)
OAS_prob.add_constraint('tail_perf.CL', equals=0.5)
# Actually run the problem
OAS_prob.run()
print("\nWing CL:", OAS_prob.prob['wing_perf.CL'])
print("Wing CD:", OAS_prob.prob['wing_perf.CD'])