def main():
interp = ViternaAirfoil().create_akima('mh117',
Re_scaling=False,
extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]],
axis=-1)
y = interp(x)
y.shape = shape + (2, )
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp) * np.pi / 180.
pitch = 0.
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4 * 287.058 * 300.) # meters/second
rho0 = 1.4 * 98600. / (c0 * c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_discrete_input('B', val=num_blades)
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter',
val=hub_diameter,
shape=num_nodes,
units='cm')
comp.add_output('prop_diameter',
val=prop_diameter,
shape=num_nodes,
units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes,
num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group',
comp,
promotes_inputs=[
'hub_diameter', 'prop_diameter', 'chord_dv', 'theta_dv', 'pitch'
],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = CCBladeGroup(num_nodes=num_nodes,
num_radial=num_radial,
airfoil_interp=ccblade_interp,
turbine=False,
phi_residual_solve_nonlinear=False)
prob.model.add_subsystem('ccblade_group',
comp,
promotes_inputs=[
'B', 'radii', 'dradii', 'chord', 'theta',
'rho', 'mu', 'asound', 'v', 'precone',
'omega', 'hub_diameter', 'prop_diameter'
],
promotes_outputs=[('Np', 'ccblade_normal_load'),
('Tp', 'ccblade_circum_load')])
prob.setup()
prob.final_setup()
eps = 1e-2
num_phi = 45
phi = np.linspace(-0.5 * np.pi + eps, 0.0 - eps, num_phi)
phi = np.tile(phi[:, np.newaxis, np.newaxis], (1, num_nodes, num_radial))
phi_residual = np.zeros_like(phi)
for i in range(num_phi):
p = phi[i, :, :]
prob.set_val('ccblade_group.ccblade_comp.phi', p, units='rad')
prob.run_model()
prob.model.run_apply_nonlinear()
inputs, outputs, residuals = prob.model.get_nonlinear_vectors()
phi_residual[i, :, :] = residuals['ccblade_group.ccblade_comp.phi']
make_individual_plots(prob, phi, phi_residual, 'phi_residual-r{:02d}.png')
def main():
interp = ViternaAirfoil().create_akima('mh117',
Re_scaling=False,
extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]],
axis=-1)
y = interp(x)
y.shape = shape + (2, )
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp) * np.pi / 180.
pitch = 0.
prop_data = {
'num_radial': num_radial,
'num_cp': num_cp,
'pitch': pitch,
'chord': chord,
'theta': theta,
'spline_type': 'akima',
'B': num_blades,
'interp': interp
}
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4 * 287.058 * 300.) # meters/second
rho0 = 1.4 * 98600. / (c0 * c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_discrete_input('B', val=num_blades)
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter',
val=hub_diameter,
shape=num_nodes,
units='cm')
comp.add_output('prop_diameter',
val=prop_diameter,
shape=num_nodes,
units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('inputs_comp', comp, promotes=['*'])
prob.model.add_subsystem('bemt_group',
BEMTGroup(num_nodes=num_nodes,
prop_data=prop_data),
promotes_inputs=[
'rho', 'mu', 'v', 'alpha', 'incidence',
'omega', 'hub_diameter', 'prop_diameter',
'pitch', 'chord_dv', 'theta_dv'
],
promotes_outputs=[
('normal_load_dist', 'openbemt_normal_load'),
('circum_load_dist', 'openbemt_circum_load')
])
comp = GeometryGroup(num_nodes=num_nodes,
num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group',
comp,
promotes_inputs=[
'hub_diameter', 'prop_diameter', 'chord_dv', 'theta_dv', 'pitch'
],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = SimpleInflow(num_nodes=num_nodes, num_radial=num_radial)
prob.model.add_subsystem(
'inflow_comp',
comp,
promotes_inputs=['v', 'omega', 'radii', 'precone'],
promotes_outputs=['Vx', 'Vy'])
comp = CCBladeGroup(num_nodes=num_nodes,
num_radial=num_radial,
airfoil_interp=ccblade_interp,
turbine=False,
phi_residual_solve_nonlinear='bracketing')
prob.model.add_subsystem('ccblade_group',
comp,
promotes_inputs=[
'B', 'radii', 'dradii', 'chord', 'theta',
'rho', 'mu', 'asound', 'Vx', 'Vy', 'v',
'precone', 'omega', 'hub_diameter',
'prop_diameter'
],
promotes_outputs=[('Np', 'ccblade_normal_load'),
('Tp', 'ccblade_circum_load')])
prob.setup()
prob.final_setup()
prob.run_model()
make_plots(prob)
def main():
interp = ViternaAirfoil().create_akima(
'mh117', Re_scaling=False, extend_alpha=True)
def ccblade_interp(alpha, Re, Mach):
shape = alpha.shape
x = np.concatenate(
[
alpha.flatten()[:, np.newaxis],
Re.flatten()[:, np.newaxis]
], axis=-1)
y = interp(x)
y.shape = shape + (2,)
return y[..., 0], y[..., 1]
num_nodes = 1
num_blades = 3
num_radial = 15
num_cp = 6
chord = 10.
theta = np.linspace(65., 25., num_cp)*np.pi/180.
pitch = 0.
hub_diameter = 30. # cm
prop_diameter = 150. # cm
c0 = np.sqrt(1.4*287.058*300.) # meters/second
rho0 = 1.4*98600./(c0*c0) # kg/m^3
omega = 236.
prob = Problem()
comp = IndepVarComp()
comp.add_discrete_input('B', val=num_blades)
comp.add_output('rho', val=rho0, shape=num_nodes, units='kg/m**3')
comp.add_output('mu', val=1., shape=num_nodes, units='N/m**2*s')
comp.add_output('asound', val=c0, shape=num_nodes, units='m/s')
comp.add_output('v', val=77.2, shape=num_nodes, units='m/s')
comp.add_output('alpha', val=0., shape=num_nodes, units='rad')
comp.add_output('incidence', val=0., shape=num_nodes, units='rad')
comp.add_output('precone', val=0., units='deg')
comp.add_output('omega', val=omega, shape=num_nodes, units='rad/s')
comp.add_output('hub_diameter', val=hub_diameter, shape=num_nodes, units='cm')
comp.add_output('prop_diameter', val=prop_diameter, shape=num_nodes, units='cm')
comp.add_output('pitch', val=pitch, shape=num_nodes, units='rad')
comp.add_output('chord_dv', val=chord, shape=num_cp, units='cm')
comp.add_output('theta_dv', val=theta, shape=num_cp, units='rad')
prob.model.add_subsystem('indep_var_comp', comp, promotes=['*'])
comp = GeometryGroup(num_nodes=num_nodes, num_cp=num_cp,
num_radial=num_radial)
prob.model.add_subsystem(
'geometry_group', comp,
promotes_inputs=['hub_diameter', 'prop_diameter', 'chord_dv',
'theta_dv', 'pitch'],
promotes_outputs=['radii', 'dradii', 'chord', 'theta'])
comp = SimpleInflow(num_nodes=num_nodes, num_radial=num_radial)
prob.model.add_subsystem(
'inflow_comp', comp,
promotes_inputs=['v', 'omega', 'radii', 'precone'],
promotes_outputs=['Vx', 'Vy'])
comp = CCBladeGroup(num_nodes=num_nodes, num_radial=num_radial,
num_blades=num_blades,
airfoil_interp=ccblade_interp, turbine=False,
phi_residual_solve_nonlinear='bracketing')
prob.model.add_subsystem(
'ccblade_group', comp,
promotes_inputs=['radii', 'dradii', 'chord', 'theta', 'rho',
'mu', 'asound', 'v', 'omega', 'Vx', 'Vy', 'precone',
'hub_diameter', 'prop_diameter'],
promotes_outputs=['thrust', 'torque', 'efficiency'])
prob.model.add_design_var('chord_dv', lower=1., upper=20.,
scaler=5e-2)
prob.model.add_design_var('theta_dv',
lower=20.*np.pi/180., upper=90*np.pi/180.)
prob.model.add_objective('efficiency', scaler=-1.,)
prob.model.add_constraint('thrust', equals=700., scaler=1e-3,
indices=np.arange(num_nodes))
prob.driver = pyOptSparseDriver()
prob.driver.options['optimizer'] = 'SNOPT'
prob.setup()
prob.final_setup()
st = time.time()
prob.run_driver()
elapsed_time = time.time() - st
make_plots(prob)
return elapsed_time