class CrossSectionStructureVT(VariableTree):
"""
Container for a cross-sectional definition of the
internal structure of a blade.
"""
s = Float()
regions = List(desc='List of names of regions in the cross section')
webs = List(desc='List of names of regions in the cross section')
materials = Dict(desc='Dictionary of MaterialProps vartrees')
airfoil = VarTree(AirfoilShape(), desc='Cross sectional shape')
DPs = List(desc='Region division points (nregion + 1)')
def add_region(self, name):
self.add(name, VarTree(Region()))
self.regions.append(name)
return getattr(self, name)
def add_web(self, name):
self.add(name, VarTree(Region()))
self.webs.append(name)
return getattr(self, name)
def add_material(self, name, material):
if name in self.materials.keys():
return
else:
self.materials[name] = material
return self.materials[name]
def test_airfoilshape(self):
af = AirfoilShape(afs[0])
aff = af.redistribute(20, even=True)
self.assertEqual(
np.testing.assert_array_almost_equal(
af.LE, np.array([-1.76645007e-05,
-2.90461132e-04]), decimal=6), None)
self.assertAlmostEqual(af.sLE, 0.49898457668804924, places=6)
self.assertEqual(
np.testing.assert_array_almost_equal(aff.points,
aff_data,
decimal=6), None)
def redistribute_airfoil_example():
af = AirfoilShape(np.loadtxt('data/ffaw3301.dat'))
print 'number of points, ni: ', af.ni
print 'Airfoil leading edge (x, y): ', af.LE
print 'Airfoil leading edge curve fraction (s): ', af.sLE
plt.figure()
plt.plot(af.points[:, 0], af.points[:, 1], '-x', label='original')
# redistribute 200 points along the surface
# and let the LE cell size be determined based on curvature
aff = af.redistribute(200, dLE=True)
plt.plot(aff.points[:, 0], aff.points[:, 1], '-<', label='redistributed')
plt.plot(aff.LE[0], aff.LE[1], 'o', label='LE')
plt.legend(loc='best')
plt.axis('equal')
plt.show()
