def setUp(self):
self.startdir = os.getcwd()
self.tempdir = tempfile.mkdtemp(prefix='test_csv-')
os.chdir(self.tempdir)
self.top = top = set_as_top(Assembly())
driver = top.add('driver', SimpleCaseIterDriver())
top.add('comp1', ExecComp(exprs=['z=x+y']))
top.add('comp2', ExecComp(exprs=['z=x+1']))
top.connect('comp1.z', 'comp2.x')
top.comp1.add('a_string', Str("Hello',;','", iotype='out'))
top.comp1.add('a_array', Array(array([1.0, 3.0, 5.5]), iotype='out'))
top.comp1.add('x_array', Array(array([1.0, 1.0, 1.0]), iotype='in'))
top.comp1.add('b_bool', Bool(False, iotype='in'))
top.comp1.add('vt', VarTree(DumbVT(), iotype='out'))
top.driver.workflow.add(['comp1', 'comp2'])
# now create some Cases
outputs = ['comp1.z', 'comp2.z', 'comp1.a_string', 'comp1.a_array[2]']
cases = []
for i in range(10):
i = float(i)
inputs = [('comp1.x', i + 0.1), ('comp1.y', i * 2 + .1),
('comp1.x_array[1]', 99.88), ('comp1.b_bool', True)]
cases.append(Case(inputs=inputs, outputs=outputs))
Case.set_vartree_inputs(driver, cases)
driver.add_responses(sorted(outputs))
self.filename = "openmdao_test_csv_case_iterator.csv"
def __init__(self, num_elem=10):
super(SysAeroSurrogate, self).__init__()
# Inputs
self.add(
'alpha',
Array(np.zeros((num_elem + 1, )),
iotype='in',
desc='Angle of attack'))
self.add(
'eta',
Array(np.zeros((num_elem + 1, )),
iotype='in',
desc='Tail rotation angle'))
self.add('AR', Float(0.0, iotype='in', desc='Aspect Ratio'))
self.add('oswald', Float(0.0, iotype='in', desc="Oswald's efficiency"))
# Outputs
self.add(
'CL',
Array(np.zeros((num_elem + 1, )),
iotype='out',
desc='Lift Coefficient'))
self.add(
'CD',
Array(np.zeros((num_elem + 1, )),
iotype='out',
desc='Drag Coefficient'))
class MyComp_Full_Array(ImplicitComponent):
''' Single implicit component with 3 states and residuals, all as arrays.
For c=2.0, (x,y,z) = (1.0, -2.333333, -2.1666667)
'''
# External inputs
c = Float(
2.0,
iotype="in",
fd_step=.00001,
desc=
"arbitrary constant that is not iterated on but does affect the results"
)
# States
xx = Array(np.zeros((3)), iotype="state")
# Residuals
res = Array(np.zeros((3)), iotype="residual")
# Outputs
y_out = Float(iotype='out')
def evaluate(self):
"""run a single step to calculate the residual
values for the given state var values"""
c, x, y, z = self.c, self.xx[0], self.xx[1], self.xx[2]
self.res[0] = self.c * (3 * x + 2 * y - z) - 1
self.res[1] = 2 * x - 2 * y + 4 * z + 2
self.res[2] = -x + y / 2. - z
self.y_out = c + x + y + z
class TestAssembly(Assembly):
V = Array(iotype='in')
P = Array(iotype='in')
Prated = Float(iotype='in')
Vin = Float(iotype='in')
Vout = Float(iotype='in')
invalid_bracket_return = Float(iotype='in')
Vrated = Float(iotype='out')
def configure(self):
self.add('comp', TestComponent())
self.add('brent', Brent())
self.brent.workflow.add(['comp'])
self.driver.workflow.add(['brent'])
# connections to comp
self.connect('V', 'comp.V')
self.connect('P', 'comp.P')
self.connect('Prated', 'comp.Prated')
# setup Brent
self.connect('Vin', 'brent.lower_bound')
self.connect('Vout', 'brent.upper_bound')
self.brent.add_parameter('comp.Vrated')
self.brent.add_constraint('comp.residual = 0')
self.connect('invalid_bracket_return', 'brent.invalid_bracket_return')
# connect outputs
self.connect('comp.Vrated', 'Vrated')
def __init__(self, n=10):
super(BEMPerf, self).__init__()
#array size based on number of elements
self.add(
'delta_Ct',
Array(iotype='in',
desc='thrusts from %d different blade elements' % n,
default_value=np.ones((n, )),
shape=(n, ),
dtype=Float,
units="N"))
self.add(
'delta_Cp',
Array(iotype='in',
desc='Cp integrant points from %d different blade elements' %
n,
default_value=np.ones((n, )),
shape=(n, ),
dtype=Float))
self.add(
'lambda_r',
Array(iotype='in',
desc='lambda_r from %d different blade elements' % n,
default_value=np.ones((n, )),
shape=(n, ),
dtype=Float))
class JacketUtilOutputs(VariableTree):
"""Jacket Utilization Basic Outputs"""
t_util = Array(np.array([-9999.]),dtype=np.float, desc='Member Utilization (tensile strength)')
cb_util = Array(np.array([-9999.]),dtype=np.float, desc='Member Utilization (compression-bending buckling)')
XjntUtil = Array(np.array([-9999.]),dtype=np.float, desc='X-Joint Utilization')
KjntUtil = Array(np.array([-9999.]),dtype=np.float, desc='K-Joint Utilization')
class RNAprops(VariableTree):
"""Basic Inertial and Geometric Properties of RNA"""
mass = Float(units='kg', desc='RNA mass') #RNA mass [kg]
I = Array(np.zeros(6),
dtype=np.float,
units='kg*m**2',
desc='RNA [IXX,IYY,IZZ,IXY,IXZ,IYZ] @tower top flange')
CMoff = Array(np.zeros(3),
dtype=np.float,
units='m',
desc='RNA CM [x,y,z] offset from Tower Top Flange'
) # RNA CMx,y,zoff [m]
Thoff = Array(np.zeros(3),
dtype=np.float,
units='m',
desc='Rotor Hub Center [x,y,z] offset from Tower Top Flange'
) # Thrust point of application [m]
rna_weightM = Bool(
True,
units=None,
desc='flag to consider or not the RNA weight effect on Moment')
yawangle = Float(
0.,
units='deg',
desc=
'YAW angle CCW RH rule, to account for possible nacelle weight contribution.'
) # RNA Yaw angle [deg]
def __init__(self, num_elem=10):
super(SysSpeed, self).__init__()
# Inputs
self.add(
'temp',
Array(np.zeros((num_elem + 1, )),
iotype='in',
low=0.001,
desc='Temperature'))
self.add(
'M',
Array(np.zeros((num_elem + 1, )), iotype='in', desc='Mach Number'))
self.add('v_spline',
Array(np.zeros((num_elem + 1, )), iotype='in', desc='Speed'))
self.add(
'v_specified',
Bool(False,
iotype='in',
desc='Set to True to disable calculation and use v_spline '
'instead.'))
# Outputs
self.add('v',
Array(np.zeros((num_elem + 1, )), iotype='out', desc='Speed'))
class VarComponent(Component):
"""Contains some vars"""
boolvar = Bool(False, iotype='in')
intvar = Int(333, iotype='in')
floatvar = Float(-16.54, iotype='in')
expvar1 = Float(1.2, iotype='in')
expvar2 = Float(1.2, iotype='in')
textvar = Str("This", iotype='in')
arrayvar = Array(iotype='in')
arrayvarsplit = Array(iotype='in')
arrayvarsplit2 = Array(iotype='in')
arrayvarzerod = Array(zeros(shape=(0, 0)), iotype='in')
arrayvartwod = Array(zeros(shape=(1, 3)), iotype='in')
arraysmall = Array(iotype='in')
arrayshorthand = Array(iotype='in')
single = Array(iotype='in')
singleint = Array(iotype='in', dtype=numpy_int32)
singlebool = Array(iotype='in', dtype=bool)
stringarray = List([], iotype='in')
listenumvar = List(Enum(1, (1, 2, 3)), iotype='in')
listenumvar2 = List(Enum(1.5, (1.5, 2.4, 3.3)), iotype='in')
listenumvar3 = List(Enum('a', ('a', 'b', 'c')), iotype='in')
listenumvar4 = List(Enum(True, (True, False)), iotype='in')
def __init__(self, directory=''):
super(VarComponent, self).__init__(directory)
# Variable Containers
self.add('varcontainer', VarContainer())
class Dummy(Component):
x = Array([[-1, 1], [-2, 2]], iotype="in", shape=(2, 2))
y = Array([[-1, 1], [-2, 2]], iotype="out", shape=(2, 2))
def execute(self):
self.y = self.x
def __init__(self, func, *args, **kwargs):
super(CVwrapped, self).__init__()
self.add("frame_in", Array(iotype="in"))
self.add("frame_out", Array(iotype="out"))
self._func = func
self._args = args
self._kwargs = kwargs
def __init__(self):
super(RGBmuxer, self).__init__()
self.add("R", Array(iotype="in"))
self.add("G", Array(iotype="in"))
self.add("B", Array(iotype="in"))
self.add("frame_out", Array(iotype="out"))
class DrivenComponent(Component):
""" Just something to be driven and compute results. """
x = Array([1., 1., 1., 1.], iotype='in')
y = Array([1., 1., 1., 1.], iotype='in')
raise_error = Bool(False, iotype='in')
stop_exec = Bool(False, iotype='in')
sleep = Float(0., iotype='in')
rosen_suzuki = Float(0., iotype='out')
sum_y = Float(0., iotype='out')
extra = Float(1.5, iotype='out')
def __init__(self):
super(DrivenComponent, self).__init__()
def execute(self):
""" Compute results from input vector. """
self.extra = 2.5
if self.sleep:
time.sleep(self.sleep)
self.rosen_suzuki = rosen_suzuki(self.x)
self.sum_y = sum(self.y)
if self.raise_error:
self.raise_exception('Forced error', RuntimeError)
if self.stop_exec:
self.parent.driver.stop() # Only valid if sequential!
class HubBase(Assembly):
# variables
blade_mass = Float(iotype='in', units='kg', desc='mass of one blade')
rotor_bending_moment = Float(iotype='in',
units='N*m',
desc='flapwise bending moment at blade root')
rotor_diameter = Float(iotype='in', units='m', desc='rotor diameter')
blade_root_diameter = Float(iotype='in',
units='m',
desc='blade root diameter')
# parameters
blade_number = Int(3, iotype='in', desc='number of turbine blades')
# outputs
hub_system_mass = Float(0.0,
iotype='out',
units='kg',
desc='overall component mass')
hub_system_cm = Array(
iotype='out',
desc=
'center of mass of the hub relative to tower to in yaw-aligned c.s.')
hub_system_I = Array(
iotype='out',
desc=
'mass moments of Inertia of hub [Ixx, Iyy, Izz, Ixy, Ixz, Iyz] around its center of mass in yaw-aligned c.s.'
)
hub_mass = Float(0.0, iotype='out', units='kg')
pitch_system_mass = Float(0.0, iotype='out', units='kg')
spinner_mass = Float(0.0, iotype='out', units='kg')
class VarComponent(Component):
"""Contains some vars"""
boolvar = Bool(False, iotype='in')
intvar = Int(333, iotype='in')
floatvar = Float(-16.54, iotype='in')
expvar1 = Float(1.2, iotype='in')
expvar2 = Float(1.2, iotype='in')
textvar = Str("This", iotype='in')
arrayvar = Array(iotype='in')
arrayvarsplit = Array(iotype='in')
arrayvarsplit2 = Array(iotype='in')
arrayvarzerod = Array(zeros(shape=(0, 0)), iotype='in')
arrayvartwod = Array(zeros(shape=(1, 3)), iotype='in')
arraysmall = Array(iotype='in')
arrayshorthand = Array(iotype='in')
single = Array(iotype='in')
singleint = Array(iotype='in', dtype=numpy_int32)
singlebool = Array(iotype='in', dtype=bool)
stringarray = List([], iotype='in')
listenumvar = List(Enum(1, (1, 2, 3)), iotype='in')
listenumvar2 = List(Enum(1.5, (1.5, 2.4, 3.3)), iotype='in')
listenumvar3 = List(Enum('a', ('a', 'b', 'c')), iotype='in')
listenumvar4 = List(Enum(True, (True, False)), iotype='in')
varcontainer = VarTree(VarContainer(), iotype='in')
def __init__(self, num_elem=10):
super(SysTemp, self).__init__()
# Inputs
self.add(
'h', Array(np.zeros((num_elem + 1, )),
iotype='in',
desc='Altitude'))
# Outputs
self.add(
'temp',
Array(np.zeros((num_elem + 1, )),
iotype='out',
low=0.001,
desc='Temperature'))
self.epsilon = 500
h_lower = 11000 - self.epsilon
h_upper = 11000 + self.epsilon
matrix = np.array([[h_lower**3, h_lower**2, h_lower, 1],
[h_upper**3, h_upper**2, h_upper, 1],
[3 * h_lower**2, 2 * h_lower, 1, 0],
[3 * h_upper**2, 2 * h_upper, 1, 0]])
rhs = np.array([288.16 - (6.5e-3) * h_lower, 216.65, -6.5e-3, 0])
self.coefs = np.linalg.solve(matrix, rhs)
class SetupRunVarSpeed(Component):
"""determines approriate conditions to run AeroBase code across the power curve"""
control = VarTree(VarSpeedMachine(), iotype='in', desc='control parameters')
R = Float(iotype='in', units='m', desc='rotor radius')
npts = Int(20, iotype='in', desc='number of points to evalute aero code to generate power curve')
# outputs
Uhub = Array(iotype='out', units='m/s', desc='freestream velocities to run')
Omega = Array(iotype='out', units='rpm', desc='rotation speeds to run')
pitch = Array(iotype='out', units='deg', desc='pitch angles to run')
missing_deriv_policy = 'assume_zero'
def execute(self):
ctrl = self.control
n = self.npts
R = self.R
# # attempt to distribute points mostly before rated
# cpguess = 0.5
# Vr0 = (ctrl.ratedPower/(cpguess*0.5*rho*pi*R**2))**(1.0/3)
# Vr0 *= 1.20
# V1 = np.linspace(Vin, Vr0, 15)
# V2 = np.linspace(Vr0, Vout, 6)
# V = np.concatenate([V1, V2[1:]])
# velocity sweep
V = np.linspace(ctrl.Vin, ctrl.Vout, n)
# corresponding rotation speed
Omega_d = ctrl.tsr*V/R*RS2RPM
Omega, dOmega_dOmegad, dOmega_dmaxOmega = smooth_min(Omega_d, ctrl.maxOmega, pct_offset=0.01)
# store values
self.Uhub = V
self.Omega = Omega
self.pitch = ctrl.pitch*np.ones_like(V)
# gradients
dV = np.zeros((n, 3))
dOmega_dtsr = dOmega_dOmegad * V/R*RS2RPM
dOmega_dR = dOmega_dOmegad * -ctrl.tsr*V/R**2*RS2RPM
dOmega = hstack([dOmega_dtsr, dOmega_dR, dOmega_dmaxOmega])
dpitch = np.zeros((n, 3))
self.J = vstack([dV, dOmega, dpitch])
def list_deriv_vars(self):
inputs = ('control.tsr', 'R', 'control.maxOmega')
outputs = ('Uhub', 'Omega', 'pitch')
return inputs, outputs
def provideJ(self):
return self.J
class MyComp(Component):
x = Array([0, 0], iotype="in", dtype=float)
y = Array([0, 0], iotype="out", dtype=float)
def execute(self):
self.y = self.x**2
def common_io(assembly, varspeed, varpitch):
regulated = varspeed or varpitch
# add inputs
assembly.add('npts_coarse_power_curve', Int(20, iotype='in', desc='number of points to evaluate aero analysis at'))
assembly.add('npts_spline_power_curve', Int(200, iotype='in', desc='number of points to use in fitting spline to power curve'))
assembly.add('AEP_loss_factor', Float(1.0, iotype='in', desc='availability and other losses (soiling, array, etc.)'))
if varspeed:
assembly.add('control', VarTree(VarSpeedMachine(), iotype='in', desc='control parameters'))
else:
assembly.add('control', VarTree(FixedSpeedMachine(), iotype='in', desc='control parameters'))
# add slots (must replace)
assembly.add('geom', Slot(GeomtrySetupBase))
assembly.add('analysis', Slot(AeroBase))
assembly.add('dt', Slot(DrivetrainLossesBase))
assembly.add('cdf', Slot(CDFBase))
# add outputs
assembly.add('AEP', Float(iotype='out', units='kW*h', desc='annual energy production'))
assembly.add('V', Array(iotype='out', units='m/s', desc='wind speeds (power curve)'))
assembly.add('P', Array(iotype='out', units='W', desc='power (power curve)'))
assembly.add('diameter', Float(iotype='out', units='m', desc='rotor diameter'))
if regulated:
assembly.add('ratedConditions', VarTree(RatedConditions(), iotype='out'))
class Oneout(Component):
""" A simple output component """
# pressure units
ratio1 = Float(1.00, iotype='out',
desc='Float Variable',units='Pa') # pressure units
ratio2 = Float(1, iotype='out',
desc='Float variable', units= 'mi') # Mile
ratio3 = Float(1, iotype='out',
desc='Float variable', units= 'degF') # temperature in F
ratio4 = Float(8.314472, iotype='out',
desc='Float variable ',units='J/(mol*degK)') # R, gas const
ratio5 = Float(1, iotype='out',
desc='Float variable', units= 'degC') # temperature in C
ratio6 = Float(1, iotype='out',
desc='Float variable', units= 'N') # force in N
ratio7 = Float(1, iotype='out',
desc='Float variable', units= 'lbf') # force in lbf
ratio8 = Float(1, iotype='out',
desc='Float variable', units= 'kg') # mass in kg
ratio9 = Float(1, iotype='out',
desc='Float variable') # no units defined
ratio10 = Float(1, iotype='out',
desc='Float variable', units= 'rad') # angle in rad
arr_in = Array([1.,2.,3.], units='ft', iotype='in')
arr_out = Array([4.,5.,6.], units='kg', iotype='out')
def __init__(self):
super(Oneout, self).__init__()
def execute(self):
"""
class PreProc(Component):
""" Dummy pre-processor. """
x_in = Array([1., 1., 1., 1.], iotype='in', low=-10, high=99)
x_out = Array(iotype='out')
def execute(self):
self.x_out = self.x_in
def __init__(self, num_elem=10):
super(SysRho, self).__init__()
# Inputs
self.add('temp', Array(np.zeros((num_elem+1, )), iotype='in',
desc = 'Temperature'))
self.add('h', Array(np.zeros((num_elem+1, )), iotype='in',
desc = 'Altitude'))
# Outputs
self.add('rho', Array(np.zeros((num_elem+1, )), iotype='out', low=0.001,
desc = 'Density'))
self.epsilon = 500
h_lower = 11000 - self.epsilon
h_upper = 11000 + self.epsilon
matrix = np.array([[h_lower**3, h_lower**2, h_lower, 1],
[h_upper**3, h_upper**2, h_upper, 1],
[3*h_lower**2, 2*h_lower, 1, 0],
[3*h_upper**2, 2*h_upper, 1, 0]])
rhs = np.array([101325*(1-0.0065*h_lower/288.16)**5.2561,
22632*np.exp(-9.81*self.epsilon/(288*216.65)),
(-101325*5.2561*(0.0065/288.16)*
(1-0.0065*h_lower/288.15)**4.2561),
(22632*(-9.81/(288*216.65))*
np.exp(-9.81*self.epsilon/(288*216.65)))])
self.coefs = np.linalg.solve(matrix, rhs)
class AComp(Component):
x = Array([[1.0, 3.0], [-2.0, 4.0]], iotype='in')
y = Array(np.zeros((2, 2)), iotype='out')
def __init__(self):
super(AComp, self).__init__()
self.J = np.array([[3.5, -2.5, 1.5, 4.0],
[4.0, 2.0, -1.1, 3.4], [7.7, 6.6, 4.4, 1.1],
[0.1, 3.3, 6.8, -5.5]])
def execute(self):
""" Run arraycomp"""
y = self.J.dot(self.x.flatten())
self.y = y.reshape((2, 2))
def list_deriv_vars(self):
""" x and y """
input_keys = ('x', )
output_keys = ('y', )
return input_keys, output_keys
def provideJ(self):
"""Analytical first derivatives"""
return self.J
def configure(self):
self.add("X", Array(np.zeros(self.m), iotype="in"))
self.add("roots", Array(np.zeros(self.m), iotype="in"))
if not len(self.idx):
num_vars = np.random.randint(2, self.m)
self.idx = np.random.choice(range(self.m), num_vars,
replace=False),
def test_array_1D(self):
self.model.c1.add('y_a', Array(iotype='out'))
self.model.c1.y_a = array([1.0, 2.0])
self.model.c2.add('x_a', Array(iotype='in'))
self.model.c2.x_a = array([3.0, 6.0])
self.model.connect('c1.y_a', 'c2.x_a')
self.model.connect('c2.y', 'c1.x')
self.model.driver.workflow.initialize_residual()
self.model.run()
indep = self.model.driver.workflow.get_independents()
self.assertEqual(indep[0], 1.0)
self.assertEqual(indep[1], 2.0)
dep = self.model.driver.workflow.get_dependents()
self.assertEqual(dep[0], 0.0)
self.assertEqual(dep[1], 0.0)
dv = array([3.0, 5.0])
self.model.driver.workflow.set_independents(dv)
indep = self.model.driver.workflow.get_independents()
self.assertEqual(indep[0], 3.0)
self.assertEqual(indep[1], 5.0)
class MIMOEquation(Component):
"""Equation with 2 inputs and 2 outputs"""
# pylint: disable-msg=E1101
x = Array([1., 1., 1., 1., 1.],
iotype='in',
desc='Global Design Variables')
f1 = Float(iotype='out', desc='Output of this Discipline')
f2 = Float(iotype='out', desc='Output of this Discipline')
f3 = Float(iotype='out', desc='Output of this Discipline')
f4 = Float(iotype='out', desc='Output of this Discipline')
f5 = Float(iotype='out', desc='Output of this Discipline')
ff = Array([0., 0., 0., 0., 0.], iotype='out')
def execute(self):
"""Should converge to x=[0,0,0,0,0]"""
d = numpy.array([3, 2, 1.5, 1, 0.5])
c = 0.01
self.ff = -d * self.x - c * self.x**3
self.f1 = self.ff[0]
self.f2 = self.ff[1]
self.f3 = self.ff[2]
self.f4 = self.ff[3]
self.f5 = self.ff[4]
def test_full_matrix(self):
self.model.c1.add('y_a', Array(iotype='out'))
self.model.c1.y_a = array([[1.0, 2.0], [3.0, 4.0]])
self.model.c2.add('x_a', Array(iotype='in'))
self.model.c2.x_a = array([[2.0, 5.0], [11.0, 17.0]])
self.model.connect('c1.y_a', 'c2.x_a')
self.model.connect('c2.y', 'c1.x')
self.model.driver.workflow.initialize_residual()
self.model.run()
dv = array([3.0, 5.0, -8.0, -13.0])
self.model.driver.workflow.set_independents(dv)
indep = self.model.driver.workflow.get_independents()
self.assertEqual(indep[0], 3.0)
self.assertEqual(indep[1], 5.0)
self.assertEqual(indep[2], -8.0)
self.assertEqual(indep[3], -13.0)
dep = self.model.driver.workflow.get_dependents()
self.assertEqual(dep[0], -2.0)
self.assertEqual(dep[1], -3.0)
self.assertEqual(dep[2], 11.0)
self.assertEqual(dep[3], 17.0)
def __init__(self, n_x=None):
"""Initialize pyopt
n_x: number of design variables"""
super(pyOptSparseDriver, self).__init__()
#create lb and ub inputs so external components can set the bounds
self.n_x = None
if n_x is not None:
shape = (n_x, )
self.n_x = n_x
self.add(
'lb',
Array(
np.zeros(shape),
iotype="in",
desc=
"lower bounds for the design variables, which will override values given in the add_parameter",
shape=shape))
self.add(
'ub',
Array(
np.zeros(shape),
iotype="in",
desc=
"upper bounds for the design variables, which will override values given in the add_parameter",
shape=shape))
self.pyOpt_solution = None
self.param_type = {}
self.nparam = None
self.objs = None
self.nlcons = None
self.lin_jacs = {}
class Dummy(Component):
x = Array([[-1., 1.],[-2., 2.]],iotype="in",shape=(2,2), dtype='f')
y = Array([[-1., 1.],[-2., 2.]],iotype="out",shape=(2,2), dtype='f')
def execute(self):
self.y = self.x
class InducedVelocity(Component):
vc = Float(iotype="in")
rho = Float(iotype="in")
b = Float(iotype="in")
R = Float(iotype="in")
h = Float(iotype="in")
Ns = Int(iotype="in")
dT = Array(iotype="in")
r = Array(iotype="in")
dr = Array(iotype="in")
vi = Array(iotype="out")
def execute(self):
self.vi = np.zeros(self.Ns)
sqrt = np.zeros(self.Ns)
sqrt = 0.25 * self.b * self.dT / (np.pi * self.rho * self.r * self.dr)
sqrt += 0.25 * self.vc**2
sqrt = np.sqrt(sqrt)
self.vi += -0.5 * self.vc
self.vi += sqrt
self.vi /= (1. + (self.R / self.h / 4.)**2)
def __init__(self, iotype, client, rpath, typ):
ProxyMixin.__init__(self, client, rpath)
self._type = typ
default = self._value = self._parse(self._valstr)
desc = client.get(rpath+'.description')
if typ == float:
as_units = client.get(rpath+'.units')
if as_units:
om_units = get_translation(as_units)
else:
om_units = None
if typ != str:
if client.get(rpath+'.hasUpperBound') == 'true':
high = typ(client.get(rpath+'.upperBound'))
else:
high = None
if client.get(rpath+'.hasLowerBound') == 'true':
low = typ(client.get(rpath+'.lowerBound'))
else:
low = None
if typ == float:
Array.__init__(self, dtype=typ, iotype=iotype, desc=desc,
default_value=default, low=low, high=high,
units=om_units)
elif typ == int:
Array.__init__(self, dtype=typ, iotype=iotype, desc=desc,
default_value=default, low=low, high=high)
else:
# FIXME: This will pickle, but not unpickle.
# Probabably don't want fixed max-length string storage anyway.
Array.__init__(self, dtype=typ, iotype=iotype, desc=desc,
default_value=default)
