def test(self):
wing_dict = {'name': 'wing', 'num_y': 7, 'num_x': 2, 'symmetry': True}
tail_dict = {'name': 'tail', 'num_y': 5, 'num_x': 3, 'symmetry': False}
surfaces = [wing_dict, tail_dict]
comp = MomentCoefficient(surfaces=surfaces)
run_test(self, comp)
def setup(self):
surfaces = self.options['surfaces']
if not self.options['user_specified_Sref']:
self.add_subsystem('sum_areas',
SumAreas(surfaces=surfaces),
promotes_inputs=['*S_ref'],
promotes_outputs=['S_ref_total'])
if self.options['internally_connect_fuelburn']:
promote_fuelburn = ['fuelburn']
else:
promote_fuelburn = []
self.add_subsystem(
'CL_CD',
TotalLiftDrag(surfaces=surfaces),
promotes_inputs=['*CL', '*CD', '*S_ref', 'S_ref_total'],
promotes_outputs=['CL', 'CD'])
self.add_subsystem('fuelburn',
BreguetRange(surfaces=surfaces),
promotes_inputs=[
'*structural_weight', 'CL', 'CD', 'CT',
'speed_of_sound', 'R', 'Mach_number', 'W0',
'load_factor'
],
promotes_outputs=['fuelburn'])
self.add_subsystem('L_equals_W',
Equilibrium(surfaces=surfaces),
promotes_inputs=[
'CL', '*structural_weight', 'S_ref_total', 'W0',
'load_factor', 'rho', 'v'
] + promote_fuelburn,
promotes_outputs=['L_equals_W', 'total_weight'])
self.add_subsystem('CG',
CenterOfGravity(surfaces=surfaces),
promotes_inputs=[
'*structural_weight', '*cg_location',
'total_weight', 'W0', 'empty_cg', 'load_factor'
] + promote_fuelburn,
promotes_outputs=['cg'])
self.add_subsystem('moment',
MomentCoefficient(surfaces=surfaces),
promotes_inputs=[
'v', 'rho', 'cg', 'S_ref_total', '*b_pts',
'*widths', '*chords', '*sec_forces', '*S_ref'
],
promotes_outputs=['CM'])
def setup(self):
surfaces = self.options['surfaces']
self.add_subsystem('sum_areas',
SumAreas(surfaces=surfaces),
promotes_inputs=['*S_ref'],
promotes_outputs=['S_ref_total'])
self.add_subsystem(
'CL_CD',
TotalLiftDrag(surfaces=surfaces),
promotes_inputs=['*CL', '*CD', '*S_ref', 'S_ref_total'],
promotes_outputs=['CL', 'CD'])
self.add_subsystem('fuelburn',
BreguetRange(surfaces=surfaces),
promotes_inputs=[
'*structural_weight', 'CL', 'CD', 'CT', 'a',
'R', 'M', 'W0', 'load_factor'
],
promotes_outputs=['fuelburn'])
self.add_subsystem('L_equals_W',
Equilibrium(surfaces=surfaces),
promotes_inputs=[
'*L', '*structural_weight', 'S_ref_total',
'fuelburn', 'W0', 'load_factor', 'rho', 'v'
],
promotes_outputs=['L_equals_W', 'total_weight'])
self.add_subsystem('CG',
CenterOfGravity(surfaces=surfaces),
promotes_inputs=[
'*structural_weight', '*cg_location',
'fuelburn', 'total_weight', 'W0', 'empty_cg',
'load_factor'
],
promotes_outputs=['cg'])
self.add_subsystem('moment',
MomentCoefficient(surfaces=surfaces),
promotes_inputs=[
'v', 'rho', 'cg', 'S_ref_total', '*b_pts',
'*widths', '*chords', '*sec_forces', '*S_ref'
],
promotes_outputs=['CM'])
def test2(self):
surfaces = get_default_surfaces()
group = Group()
comp = MomentCoefficient(surfaces=surfaces)
indep_var_comp = IndepVarComp()
indep_var_comp.add_output('S_ref_total', val=1e4, units='m**2')
group.add_subsystem('moment_calc', comp)
group.add_subsystem('indep_var_comp', indep_var_comp)
group.connect('indep_var_comp.S_ref_total', 'moment_calc.S_ref_total')
run_test(self, group)
def test(self):
wing_dict = {
'name': 'wing',
'mesh': np.zeros((2, 7)),
'symmetry': True
}
tail_dict = {
'name': 'tail',
'mesh': np.zeros((3, 5)),
'symmetry': False
}
surfaces = [wing_dict, tail_dict]
comp = MomentCoefficient(surfaces=surfaces)
run_test(self, comp)
def setup(self):
surfaces = self.options['surfaces']
self.add_subsystem('sum_areas',
SumAreas(surfaces=surfaces),
promotes_inputs=['*S_ref'],
promotes_outputs=['S_ref_total'])
self.add_subsystem(
'CL_CD',
TotalLiftDrag(surfaces=surfaces),
promotes_inputs=['*CL', '*CD', '*S_ref', 'S_ref_total'],
promotes_outputs=['CL', 'CD'])
self.add_subsystem('moment',
MomentCoefficient(surfaces=surfaces),
promotes_inputs=[
'v', 'cg', 'rho', '*S_ref', '*b_pts', '*widths',
'*chords', '*sec_forces', 'S_ref_total'
],
promotes_outputs=['CM'])