import matplotlib
matplotlib.use('Agg')
from matplotlib import pyplot as plt
import numpy as np
import paraBEM
from paraBEM.pan2d import DirichletDoublet0Source0Case2 as Case
from paraBEM.airfoil import Airfoil
from paraBEM.utils import check_path
a = Airfoil.trefftz_kutta(-0.1 + 0.01j, np.deg2rad(2), 51)
alpha_list = np.deg2rad(np.linspace(-15, 30, 30))
cl = []
cd = []
cm = []
xcp = []
for alpha in alpha_list:
case = Case(a.panels)
case.v_inf = paraBEM.Vector2(np.cos(alpha), np.sin(alpha))
case.mom_ref_point = paraBEM.Vector2(-0, -3)
case.run()
cl.append(case.cl)
cd.append(case.force.dot(case.v_inf) * 10)
cm.append(case.cm)
# xcp.append(case.center_of_pressure.x)
del (case)
plt.plot(cl, alpha_list, color="black", linestyle="-", label="cl")
plt.plot(cm, alpha_list, color="black", dashes=[8, 4, 2, 4, 2, 4], label="cm")
# -*- coding: utf-8 -*- import numpy as np import paraBEM from paraBEM.airfoil import Airfoil from paraBEM.utils import check_path from paraBEM.vtk_export import VtkWriter from paraBEM.pan2d import DirichletDoublet1Case2 as Case # geometry airfoil = Airfoil.trefftz_kutta(-0.1 + 0.0j, np.deg2rad(30)) airfoil.numpoints = 50 points = [paraBEM.PanelVector2(*i) for i in airfoil.coordinates[:-1]] points[0].wake_vertex = True panels = [paraBEM.Panel2([coord, points[i+1]]) for i, coord in enumerate(points[:-1])] panels.append(paraBEM.Panel2([points[-1], points[0]])) # panelmethode case = Case(panels) case.v_inf = paraBEM.Vector2(1, 0.3) case.run() # plt.plot(np.array(case.matrix.values).T) # # plt.show() nx = 200 ny = 200 space_x = np.linspace(-0.2, 1.5, nx) space_y = np.linspace(-0.5, 0.5, ny) grid = [paraBEM.Vector2(x, y) for y in space_y for x in space_x] velocity = list(map(case.off_body_velocity, grid))
# -*- coding: utf-8 -*-
import numpy as np
import paraBEM
from paraBEM.airfoil import Airfoil
from paraBEM.utils import check_path
from paraBEM.vtk_export import VtkWriter
from paraBEM.pan2d import DirichletDoublet1Case2 as Case
# geometry
airfoil = Airfoil.trefftz_kutta(-0.1 + 0.0j, np.deg2rad(30))
airfoil.numpoints = 50
points = [paraBEM.PanelVector2(*i) for i in airfoil.coordinates[:-1]]
points[0].wake_vertex = True
panels = [
paraBEM.Panel2([coord, points[i + 1]])
for i, coord in enumerate(points[:-1])
]
panels.append(paraBEM.Panel2([points[-1], points[0]]))
# panelmethode
case = Case(panels)
case.v_inf = paraBEM.Vector2(1, 0.3)
case.run()
# plt.plot(np.array(case.matrix.values).T)
# # plt.show()
nx = 200
ny = 200
space_x = np.linspace(-0.2, 1.5, nx)
space_y = np.linspace(-0.5, 0.5, ny)
