def test_from_list(self):
dat = AirfoilPoints.from_list(
'test', [[1, 0.5], [0.5, 0.5], [0, 0], [0.5, -0.5]])
self.assertEqual(dat.positions[0].surface, Surfaces.TOP)
self.assertEqual(dat.positions[-1].surface, Surfaces.BTM)
def test_from_airfoiltools(self):
dat = AirfoilPoints.from_airfoiltools('naca2411-il')
self.assertEqual(dat.chord, 1)
def test_set_te_thick(self):
dat = AirfoilPoints.from_file(
'test//test_airfoil.dat').set_te_thickness(0.1)
self.assertEqual(dat.te_thickness, .1)
def test_set_chord(self):
dat = AirfoilPoints.from_file('test//test_airfoil.dat').set_chord(2)
self.assertEqual(dat.chord, 2)
def test_measurements(self):
dat = AirfoilPoints.from_file('test//test_airfoil.dat')
self.assertEqual(dat.chord, 1)
self.assertEqual(dat.te_thickness,
dat.positions[0].y - dat.positions[-1].y)
self.assertEqual(dat.thickness, 0.14121)
def test_from_file(self):
dat = AirfoilPoints.from_file('test//test_airfoil.dat')
self.assertEqual(dat.positions[0].surface, Surfaces.TOP)
self.assertEqual(dat.positions[-1].surface, Surfaces.BTM)