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 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)
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 redistribute(self, points, pos_z):
if self.redistribute_flag == False:
return points
airfoil = AirfoilShape(points=points)
try:
dist_LE = np.interp(pos_z, self.dist_LE[:, 0], self.dist_LE[:, 1])
except:
dist_LE = None
# pass airfoil to user defined routine to allow for additional configuration
airfoil = self.set_airfoil(airfoil, pos_z)
if self.x_chordwise.shape[0] > 0:
airfoil = airfoil.redistribute_chordwise(self.x_chordwise)
else:
airfoil = airfoil.redistribute(ni=self.chord_ni, dLE=dist_LE)
return airfoil.points
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()
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()
