for reduced_frequency in reduced_freq_domain:
i += 1
# reduced_frequency = 0.25
# M, N, Mstarfact = 8, 4, 50
M, N, Mstarfact = 12, 16, 50
u_inf = 20
alpha = 0
AR = 30
rho = 1.225
ws = flying_wings.Goland(M=M,
N=N,
Mstar_fact=Mstarfact,
u_inf=u_inf,
alpha=alpha,
rho=rho,
aspect_ratio=AR,
case_name='sears',
route='./cases')
gust_length = np.pi * ws.c_ref / reduced_frequency
gust_intensity = 0.01
N_periods = 4
omega = reduced_frequency * 2 * u_inf / ws.c_ref
period = 2 * np.pi / omega
ws.physical_time = N_periods * period
for sim_type in ['nlin', 'lin']:
import cases.templates.flying_wings as wings
import sharpy.sharpy_main
aero_type = 'lin'
ws = wings.Goland(M=4,
N=12,
Mstar_fact=10,
u_inf=50,
alpha=1.,
rho=1.225,
sweep=0,
physical_time=2,
n_surfaces=2,
route='cases',
case_name='goland_' + aero_type + '_newsolver_pred')
ws.gust_intensity = 0.01
# ws.n_tstep = 2
ws.sigma = 1
ws.clean_test_files()
ws.update_derived_params()
ws.update_aero_prop()
ws.update_fem_prop()
ws.set_default_config_dict()
ws.generate_aero_file()
ws.generate_fem_file()
ws.config['SHARPy']['flow'] = [
'BeamLoader',
def set_up_test_case(self, aero_type, predictor, sparse, integration_order):
# aero_type = 'lin'
global case_name
case_name = 'goland_' + aero_type + '_'+'P%g_S%g_I%g' %(predictor, sparse, integration_order)
ws = wings.Goland(M=12,
N=4,
Mstar_fact=50,
u_inf=50,
alpha=1.,
rho=1.225,
sweep=0,
physical_time=0.1,
n_surfaces=2,
route='cases',
case_name=case_name)
# Other test parameters
ws.gust_intensity = 0.01
ws.sigma = 1
ws.dt_factor = 1
ws.clean_test_files()
ws.update_derived_params()
ws.update_aero_prop()
ws.update_fem_prop()
ws.set_default_config_dict()
ws.generate_aero_file()
ws.generate_fem_file()
ws.config['SHARPy']['flow'] = ['BeamLoader', 'AerogridLoader',
'StaticCoupled',
'DynamicCoupled']
ws.config['SHARPy']['write_screen'] = 'off'
# Remove newmark damping from structural solver settings
ws.config['DynamicCoupled']['structural_solver_settings']['newmark_damp'] = 0
if aero_type == 'lin':
ws.config['DynamicCoupled']['aero_solver'] = 'StepLinearUVLM'
ws.config['DynamicCoupled']['aero_solver_settings'] = {'dt': ws.dt,
'remove_predictor': predictor,
'use_sparse': sparse,
'integr_order': integration_order,
'velocity_field_generator': 'GustVelocityField',
'velocity_field_input': {'u_inf': ws.u_inf,
'u_inf_direction': [1., 0.,
0.],
'gust_shape': 'continuous_sin',
'offset': 2.,
'gust_parameters': {'gust_length': 2.,
'gust_intensity': ws.gust_intensity
* ws.u_inf,
'span': ws.main_chord * ws.aspect_ratio}}}
else:
ws.config['DynamicCoupled']['aero_solver'] = 'StepUvlm'
ws.config['DynamicCoupled']['aero_solver_settings'] = {
'print_info': 'off',
'horseshoe': True,
'num_cores': 4,
'n_rollup': 100,
'convection_scheme': 0,
'rollup_dt': ws.dt,
'rollup_aic_refresh': 1,
'rollup_tolerance': 1e-4,
'velocity_field_generator': 'GustVelocityField',
'velocity_field_input': {'u_inf': ws.u_inf,
'u_inf_direction': [1., 0, 0],
'gust_shape': 'continuous_sin',
'gust_length': ws.gust_length,
'gust_intensity': ws.gust_intensity * ws.u_inf,
'offset': 2.0,
'span': ws.main_chord * ws.aspect_ratio},
'rho': ws.rho,
'n_time_steps': ws.n_tstep,
'dt': ws.dt,
'gamma_dot_filtering': 0,
'track_body': True,
'track_body_number': -1}
ws.config['DynamicCoupled']['include_unsteady_force_contribution'] = 'on'
# Update settings file
ws.config.write()
self.case_name = ws.case_name
self.case_route = ws.route
self.ws = ws
self.dt = ws.dt
case_name = 'goland'
case_nlin_info = 'M%dN%dMs%d_nmodes%d' % (M, N, M_star_fact, num_modes)
case_rom_info = 'rom_MIMORA_r%d_sig%04d_%04dj' % (
r, frequency_continuous_k[0].real * 1000,
frequency_continuous_k[0].imag * 1000)
fig_folder = './figures/'
os.system('mkdir -p %s' % fig_folder)
# SHARPy nonlinear reference solution
ws = wings.Goland(
M=M,
N=N,
Mstar_fact=M_star_fact,
u_inf=u_inf,
alpha=alpha_deg,
beta=0,
# aspect_ratio=32,
rho=rho,
sweep=0,
physical_time=2,
n_surfaces=2,
route='cases',
case_name=case_name)
ws.gust_intensity = 0.01
ws.sigma = 1
ws.clean_test_files()
ws.update_derived_params()
ws.update_aero_prop()
ws.n_tstep = 20
ws.update_fem_prop()
for ii in range(Npoints):
### update parameters
tplparams=(int(np.round(100*AlphaInfVecDeg[ii])),
int(np.round(100*AlphaVecDeg[ii])),
int(np.round(100*SideVecDeg[ii])) ,
int(np.round(100*RollVecDeg[ii])) )
case_here=case_main+'_ainf%.4da%.4ds%.4dr%.4d'%tplparams
route_here=route_main
os.system('mkdir -p %s'%(route_here,))
### ------------------------------------------------------ Build wing model
ws=flying_wings.Goland( M=M,N=N,Mstar_fact=Mstar_fact,n_surfaces=Nsurf,
u_inf=u_inf,
alpha=AlphaVecDeg[ii],
beta=-SideVecDeg[ii],
route=route_here,
case_name=case_here)
# updte wind direction
quat_wind=algebra.euler2quat(-np.pi/180.*np.array([0.,AlphaInfVecDeg[ii],0.]))
u_inf_dir=np.dot( algebra.quat2rotation(quat_wind),np.array([1.,0.,0.]))
ws.main_ea-=.25/M
ws.main_cg-=.25/M
ws.root_airfoil_P = 4
ws.root_airfoil_M = 2
ws.tip_airfoil_P = 4
ws.tip_airfoil_M = 2
ws.clean_test_files()
# Case Admin
case_route = os.path.abspath('.')
results_folder = case_route + '/res/'
fig_folder = case_route + '/figs/'
os.system('mkdir -p %s' % results_folder)
os.system('mkdir -p %s' % fig_folder)
case_name = 'sears_uinf%04d_AR%02d_M%dN%dMs%d_KR%d_sp%i' % (
u_inf, AR, M, N, MstarFact, krylov_r, use_sparse)
# Wing model
ws = wings.Goland(M=M,
N=N,
Mstar_fact=MstarFact,
n_surfaces=nsurf,
u_inf=u_inf,
rho=rho,
alpha=alpha_deg,
aspect_ratio=AR,
route=results_folder,
case_name=case_name)
ws.main_ea = main_ea
ws.clean_test_files()
ws.update_derived_params()
ws.generate_fem_file()
ws.generate_aero_file()
# Solution settings
ws.set_default_config_dict()
ws.config['SHARPy']['flow'] = [
# ------------------------------------------------ Build solution at UinfVec[0]
# This is used for creating the reference (normalised) UVLM
### Reference geometrically-exact solution (linearisation & scaling point)
u_inf=Uinf0
case_here=case_main+'_a%.4d_uinf%.4d'%( int(np.round(100*Alpha0Deg)), 10*u_inf)
route_here=route_main+'a%.4d/'%int(np.round(100*Alpha0Deg))
os.system('mkdir -p %s'%(route_here,))
# Build wing model
ws=flying_wings.Goland(M=M,N=N,Mstar_fact=Mstar_fact,
n_surfaces=Nsurf,
alpha=Alpha0Deg,
roll=Roll0Deg,
RollNodes=RollNodes,
u_inf=u_inf,
route=route_here,
case_name=case_here)
ws.clean_test_files()
ws.update_derived_params()
ws.generate_fem_file()
ws.generate_aero_file()
# solution flow
ws.set_default_config_dict()
ws.config['SHARPy']['flow']=[
'BeamLoader', 'AerogridLoader', 'StaticUvlm', 'Modal', 'SaveData']
ws.config['SaveData']={'folder': route_here}
ws.config['LinearUvlm'] = { 'dt': ws.dt,
def setUp(self):
# Problem Set up
u_inf = 1.
alpha_deg = 0.
rho = 1.02
num_modes = 4
# Lattice Discretisation
M = 4
N = 8
M_star_fact = 1
# Linear UVLM settings
integration_order = 2
remove_predictor = False
use_sparse = False
# Case Admin - Create results folders
case_name = 'goland_cs'
case_nlin_info = 'M%dN%dMs%d_nmodes%d' % (M, N, M_star_fact, num_modes)
case_name += case_nlin_info
self.route_test_dir = os.path.abspath(
os.path.dirname(os.path.realpath(__file__)))
fig_folder = self.route_test_dir + '/figures/'
os.makedirs(fig_folder, exist_ok=True)
# SHARPy nonlinear reference solution
ws = wings.Goland(M=M,
N=N,
Mstar_fact=M_star_fact,
u_inf=u_inf,
alpha=alpha_deg,
rho=rho,
sweep=0,
physical_time=2,
n_surfaces=2,
route=self.route_test_dir + '/cases',
case_name=case_name)
ws.gust_intensity = 0.01
ws.sigma = 1
ws.horseshoe = True
ws.clean_test_files()
ws.update_derived_params()
ws.set_default_config_dict()
ws.generate_aero_file()
ws.generate_fem_file()
ws.config['SHARPy'] = {
'flow': [
'BeamLoader',
'AerogridLoader',
'StaticCoupled',
'AerogridPlot',
'BeamPlot',
'Modal',
'LinearAssembler',
'FrequencyResponse',
],
'case':
ws.case_name,
'route':
ws.route,
'write_screen':
'off',
'write_log':
'on',
'log_folder':
self.route_test_dir + '/output/' + ws.case_name + '/',
'log_file':
ws.case_name + '.log'
}
ws.config['BeamLoader'] = {'unsteady': 'off', 'orientation': ws.quat}
ws.config['AerogridLoader'] = {
'unsteady': 'off',
'aligned_grid': 'on',
'mstar': 1,
'freestream_dir': ws.u_inf_direction
}
ws.config['StaticUvlm'] = {
'rho': ws.rho,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {
'u_inf': ws.u_inf,
'u_inf_direction': ws.u_inf_direction
},
'rollup_dt': ws.dt,
'print_info': 'on',
'horseshoe': 'off',
'num_cores': 4,
'n_rollup': 0,
'rollup_aic_refresh': 0,
'rollup_tolerance': 1e-4
}
ws.config['StaticCoupled'] = {
'print_info': 'on',
'max_iter': 200,
'n_load_steps': 1,
'tolerance': 1e-10,
'relaxation_factor': 0.,
'aero_solver': 'StaticUvlm',
'aero_solver_settings': {
'rho': ws.rho,
'print_info': 'off',
'horseshoe': 'off',
'num_cores': 4,
'n_rollup': 0,
'rollup_dt': ws.dt,
'rollup_aic_refresh': 1,
'rollup_tolerance': 1e-4,
'velocity_field_generator': 'SteadyVelocityField',
'velocity_field_input': {
'u_inf': ws.u_inf,
'u_inf_direction': ws.u_inf_direction
}
},
'structural_solver': 'NonLinearStatic',
'structural_solver_settings': {
'print_info': 'off',
'max_iterations': 150,
'num_load_steps': 4,
'delta_curved': 1e-1,
'min_delta': 1e-10,
'gravity_on': 'on',
'gravity': 9.754
}
}
ws.config['AerogridPlot'] = {
'folder': self.route_test_dir + '/output/',
'include_rbm': 'off',
'include_applied_forces': 'on',
'minus_m_star': 0
}
ws.config['AeroForcesCalculator'] = {
'folder': self.route_test_dir + '/output/forces',
'write_text_file': 'on',
'text_file_name': ws.case_name + '_aeroforces.csv',
'screen_output': 'on',
'unsteady': 'off'
}
ws.config['BeamPlot'] = {
'folder': self.route_test_dir + '/output/',
'include_rbm': 'off',
'include_applied_forces': 'on'
}
ws.config['BeamCsvOutput'] = {
'folder': self.route_test_dir + '/output/',
'output_pos': 'on',
'output_psi': 'on',
'screen_output': 'on'
}
ws.config['Modal'] = {
'folder': self.route_test_dir + '/output/',
'NumLambda': 20,
'rigid_body_modes': 'off',
'print_matrices': 'on',
'keep_linear_matrices': 'on',
'write_dat': 'off',
'rigid_modes_cg': 'off',
'continuous_eigenvalues': 'off',
'dt': 0,
'plot_eigenvalues': False,
'max_rotation_deg': 15.,
'max_displacement': 0.15,
'write_modes_vtk': True,
'use_undamped_modes': True
}
ws.config['LinearAssembler'] = {
'linear_system': 'LinearAeroelastic',
'linear_system_settings': {
'beam_settings': {
'modal_projection': 'on',
'inout_coords': 'modes',
'discrete_time': 'on',
'newmark_damp': 0.5e-4,
'discr_method': 'newmark',
'dt': ws.dt,
'proj_modes': 'undamped',
'use_euler': 'off',
'num_modes': num_modes,
'print_info': 'on',
'gravity': 'on',
'remove_sym_modes': 'on',
'remove_dofs': []
},
'aero_settings': {
'dt': ws.dt,
'ScalingDict': {
'length': 0.5 * ws.c_ref,
'speed': u_inf,
'density': rho
},
'integr_order': integration_order,
'density': ws.rho,
'remove_predictor': remove_predictor,
'use_sparse': use_sparse,
'rigid_body_motion': 'off',
'use_euler': 'off',
'remove_inputs': ['u_gust'],
},
'rigid_body_motion': False
}
}
ws.config['LinDynamicSim'] = {
'dt': ws.dt,
'n_tsteps': ws.n_tstep,
'sys_id': 'LinearAeroelastic',
'postprocessors': ['BeamPlot', 'AerogridPlot'],
'postprocessors_settings': {
'AerogridPlot': {
'u_inf': ws.u_inf,
'folder': self.route_test_dir + '/output/',
'include_rbm': 'on',
'include_applied_forces': 'on',
'minus_m_star': 0
},
'BeamPlot': {
'folder': ws.route + '/output/',
'include_rbm': 'on',
'include_applied_forces': 'on'
}
}
}
ws.config['FrequencyResponse'] = {
'compute_fom': 'on',
'quick_plot': 'off',
'folder': self.route_test_dir + '/output/',
'frequency_unit': 'k',
'frequency_bounds': [0.0001, 1.0],
}
self.ws = ws
