def configure_blade():
top = Assembly()
configure_bladesurface(top, planform_nC=6)
# load the planform file
top.pf_splines.pfIn = read_blade_planform(
os.path.join(PATH, 'data/DTU_10MW_RWT_blade_axis_prebend.dat'))
top.blade_length = 86.366
top.span_ni = 5
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 40
# load the airfoil shapes defining the blade
for f in [
os.path.join(PATH, 'data/ffaw3241.dat'),
os.path.join(PATH, 'data/ffaw3301.dat'),
os.path.join(PATH, 'data/ffaw3360.dat'),
os.path.join(PATH, 'data/ffaw3480.dat'),
os.path.join(PATH, 'data/cylinder.dat')
]:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 1.])
return top
def configure_blade():
top = Assembly()
configure_bladesurface(top, os.path.join(PATH, 'data/DTU_10MW_RWT_blade_axis_prebend.dat'), planform_nC=6)
# load the planform file
top.blade_length = 86.366
top.span_ni = 5
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 40
# load the airfoil shapes defining the blade
for f in [os.path.join(PATH, 'data/ffaw3241.dat'),
os.path.join(PATH, 'data/ffaw3301.dat'),
os.path.join(PATH, 'data/ffaw3360.dat'),
os.path.join(PATH, 'data/ffaw3480.dat') ,
os.path.join(PATH, 'data/cylinder.dat')]:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 1.])
return top
def lofted_blade_shape_example():
top = Assembly()
configure_bladesurface(top, planform_nC=6)
# load the planform file
top.pf_splines.pfIn = read_blade_planform('data/DTU_10MW_RWT_blade_axis_prebend.dat')
top.blade_length = 86.366
top.span_ni = 50
print 'planform variables: ', top.pf_splines.pfOut.list_vars()
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 200
# load the airfoil shapes defining the blade
for f in ['data/ffaw3241.dat',
'data/ffaw3301.dat',
'data/ffaw3360.dat',
'data/ffaw3480.dat' ,
'data/tc72.dat' ,
'data/cylinder.dat']:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 0.72, 1.])
top.run()
pf = top.pf_splines.pfOut
plt.figure()
plt.title('chord')
plt.plot(pf.s, pf.chord)
plt.savefig('chord.eps')
plt.figure()
plt.title('twist')
plt.plot(pf.s, pf.rot_z)
plt.savefig('twist.eps')
plt.figure()
plt.title('relative thickness')
plt.plot(pf.s, pf.rthick)
plt.savefig('rthick.eps')
plt.figure()
plt.title('pitch axis aft leading edge')
plt.plot(pf.s, pf.p_le)
plt.savefig('p_le.eps')
plt.figure()
plt.axis('equal')
for i in range(b.span_ni):
plt.plot(b.surfout.surface[:, i, 0], b.surfout.surface[:, i, 1])
plt.savefig('lofted_blade.eps')
return top
def lofted_blade_shape_example():
top = Assembly()
configure_bladesurface(top, 'data/DTU_10MW_RWT_blade_axis_prebend.dat', planform_nC=6)
# load the planform file
top.blade_length = 86.366
top.span_ni = 50
print 'planform variables: ', top.pf_splines.pfOut.list_vars()
b = top.blade_surface
# distribute 200 points evenly along the airfoil sections
b.chord_ni = 200
# load the airfoil shapes defining the blade
for f in ['data/ffaw3241.dat',
'data/ffaw3301.dat',
'data/ffaw3360.dat',
'data/ffaw3480.dat' ,
'data/tc72.dat' ,
'data/cylinder.dat']:
b.base_airfoils.append(np.loadtxt(f))
b.blend_var = np.array([0.241, 0.301, 0.36, 0.48, 0.72, 1.])
top.run()
pf = top.pf_splines.pfOut
plt.figure()
plt.title('chord')
plt.plot(pf.s, pf.chord)
plt.savefig('chord.eps')
plt.figure()
plt.title('twist')
plt.plot(pf.s, pf.rot_z)
plt.savefig('twist.eps')
plt.figure()
plt.title('relative thickness')
plt.plot(pf.s, pf.rthick)
plt.savefig('rthick.eps')
plt.figure()
plt.title('pitch axis aft leading edge')
plt.plot(pf.s, pf.p_le)
plt.savefig('p_le.eps')
plt.figure()
plt.axis('equal')
for i in range(b.span_ni):
plt.plot(b.surfout.surface[:, i, 0], b.surfout.surface[:, i, 1])
plt.savefig('lofted_blade.eps')
plt.savefig('lofted_blade.png')
return top
import numpy as np
from openmdao.lib.datatypes.api import VarTree
from openmdao.main.api import Assembly, Component
from fusedwind.interface import implement_base
from fusedwind.turbine.geometry import read_blade_planform, redistribute_blade_planform
from fusedwind.turbine.configurations import configure_bladestructure, configure_bladesurface
from fusedwind.turbine.blade_structure import SplinedBladeStructure
from fusedwind.turbine.structure_vt import BladeStructureVT3D
top = Assembly()
configure_bladesurface(top,
'data/DTU_10MW_RWT_blade_axis_prebend.dat',
planform_nC=6)
configure_bladestructure(top, 'data/DTU10MW', structure_nC=5)
top.st_writer.filebase = 'st_test'
top.blade_length = 86.366
top.span_ni = 30
top.blade_surface.chord_ni = 300
for f in [
'data/ffaw3241.dat', 'data/ffaw3301.dat', 'data/ffaw3360.dat',
'data/ffaw3480.dat', 'data/tc72.dat', 'data/cylinder.dat'
]:
top.blade_surface.base_airfoils.append(np.loadtxt(f))
# --- 1 -----
import numpy as np
from openmdao.lib.datatypes.api import VarTree
from openmdao.main.api import Assembly, Component
from fusedwind.interface import implement_base
from fusedwind.turbine.geometry import read_blade_planform, redistribute_blade_planform
from fusedwind.turbine.configurations import configure_bladestructure, configure_bladesurface
from fusedwind.turbine.blade_structure import SplinedBladeStructure
from fusedwind.turbine.structure_vt import BladeStructureVT3D
top = Assembly()
configure_bladesurface(top, 'data/DTU_10MW_RWT_blade_axis_prebend.dat', planform_nC=6)
configure_bladestructure(top, 'data/DTU10MW', structure_nC=5)
top.st_writer.filebase = 'st_test'
top.blade_length = 86.366
top.span_ni = 30
top.blade_surface.chord_ni = 300
for f in ['data/ffaw3241.dat',
'data/ffaw3301.dat',
'data/ffaw3360.dat',
'data/ffaw3480.dat',
'data/tc72.dat',
'data/cylinder.dat']:
