def show_pressure(self):
import paraBEM
from paraBEM.pan2d import DirichletDoublet0Source0Case2
# 1. get the panels from the airfoil
self.current_airfoil.apply_splines()
coords = self.current_airfoil.data[:-1]
pans = []
vertices = []
vertices = [paraBEM.PanelVector2(*i) for i in coords]
vertices[0].wake_vertex = True
for i, coord in enumerate(coords):
j = (i + 1 if (i + 1) < len(coords) else 0)
pan = paraBEM.Panel2([vertices[i], vertices[j]])
pans.append(pan)
# 2. compute pressure
case = DirichletDoublet0Source0Case2(pans)
alpha = np.deg2rad(self.Qalpha.value())
case.v_inf = paraBEM.Vector2(np.cos(alpha), np.sin(alpha))
case.run()
for pan in pans:
p0 = pan.center
p1 = p0 + pan.n * pan.cp * 0.03
l = [[*p0, 0.], [*p1, 0.]] # adding z-value
self.pressure_sep += pp.Line(l).object
return True
import matplotlib
matplotlib.use('Agg')
import matplotlib.pyplot as plt
import numpy as np
import paraBEM
from paraBEM.vtk_export import CaseToVTK
from paraBEM.pan2d import DirichletDoublet0Source0Case2 as Case
from paraBEM.airfoil import Airfoil
n_x = 2000
n_y = 10
a = Airfoil.import_from_dat("/home/lo/Copy/modellbau/profile/jwl/jwl044.dat")
a.numpoints = n_x
case = Case(a.panels)
case.v_inf = paraBEM.Vector2(1, 0.2)
case.run()
plt.plot(*zip(*[[pan.center.x, pan.cp] for pan in case.panels]), marker="x")
# plt.show()
