def test_lines(self):
values = np.linspace(-3, 3, 10)
return [
[Vector2(i, 0) for i in values],
[Vector2(i, i) for i in values],
[Vector2(0, i) for i in values]
]
alpha = np.deg2rad(10)
# panelmethode
coordiantes = list(
zip(
airfoil.coordinates(num=num_pan).real,
airfoil.coordinates(num=num_pan).imag))
vertices = [PanelVector2(*v) for v in coordiantes[:-1]]
vertices[0].wake_vertex = True
panels = [
Panel2([vertices[i], vertices[i + 1]]) for i in range(len(vertices[:-1]))
]
panels.append(Panel2([vertices[-1], vertices[0]]))
case = Case(panels)
case.v_inf = Vector2(np.cos(alpha), np.sin(alpha))
case.run()
nx = 500
ny = 500
space_x = np.linspace(-3, 7, nx)
space_y = np.linspace(-2, 2, ny)
vec = lambda x: paraBEM.Vector2(x[0], x[1])
vec3 = lambda x: [x[0], x[1], 0]
grid = [[x, y, 0] for y in space_y for x in space_x]
_grid = list(map(vec, grid))
velocity = list(map(vec3, list(map(case.off_body_velocity, _grid))))
vel1 = [(i[0]**2 + i[1]**2)**(0.5) for i in velocity]
pot = list(map(case.off_body_potential, _grid))
def test_element_v(self, target=Vector2(0, 0)):
return doublet_2_1_v(target, self.panel, True)
def test_element_phi(self, target=Vector2(0, 0)):
return doublet_2_0(target, self.panel)
def test_element_v(self, target=Vector2(0, 0)):
return source_2_0_v(target, self.panel)
def test_element_v(self, target=Vector2(0, 0)):
return 0, 0