def min_func(x):
global count
count += 1
print("\niteration: " + str(count))
_glider2d = deepcopy(glider2d)
glider_set_controlpoint(_glider2d, x)
glider3d = _glider2d.get_glider_3d()
panels = paraBEM_Panels(glider3d,
midribs=0,
profile_numpoints=40,
symmetric=True,
distribution=Distribution.from_nose_cos_distribution(40, 0.2),
num_average=0)
case = Case(panels[1], panels[2])
case.farfield = 5
case.drag_calc = "trefftz"
case.A_ref = 23
case.create_wake(length=10000, count=5)
case.v_inf = paraBEM.Vector3(8, 0, 1)
case.trefftz_cut_pos = case.v_inf * 50
alpha = v_inf_deg_range3(case.v_inf, 5, 9, 20)
polars = case.polars(alpha)
vtk_writer = CaseToVTK(case, "results/vtk_opt", suffix=str(count))
vtk_writer.write_panels(data_type="point")
cL = []
cD = []
for i in polars.values:
cL.append(i.cL)
cD.append(i.cD)
return np.interp(0.6, cL, cD)
def create_potential_table(self):
if not self.paraBEM:
self.QWarning = QtGui.QLabel("no panel_method installed")
self.layout.addWidget(self.QWarning)
else:
self._vertices, self._panels, self._trailing_edges = paraBEM_Panels(
self.ParametricGlider.get_glider_3d(),
midribs=0,
profile_numpoints=50,
num_average=4,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=True
)
case = self.pan3d.DirichletDoublet0Source0Case3(self._panels, self._trailing_edges)
case.A_ref = self.ParametricGlider.shape.area
case.mom_ref_point = self.paraBEM.Vector3(1.25, 0, -6)
case.v_inf = self.paraBEM.Vector(self.ParametricGlider.v_inf)
case.drag_calc = "trefftz"
case.farfield = 5
case.create_wake(10000000, 20)
pols = case.polars(self.paraBEM_utils.v_inf_deg_range3(case.v_inf, 2, 15, 20))
self.cL = []
self.cDi = []
self.cPi = []
self.alpha = []
for i in pols.values:
self.alpha.append(i.alpha)
self.cL.append(i.cL)
self.cDi.append(i.cD)
self.cPi.append(i.cP)
self.alpha = np.array(self.alpha)
self.cL = np.array(self.cL)
self.cDi = np.array(self.cDi)
self.cPi = np.array(self.cPi)
def create_potential_table(self):
if not self.paraBEM:
self.QWarning = QtGui.QLabel('no panel_method installed')
self.layout.addWidget(self.QWarning)
else:
self._vertices, self._panels, self._trailing_edges = paraBEM_Panels(
self.parametric_glider.get_glider_3d(),
midribs=0,
profile_numpoints=50,
num_average=4,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=True)
case = self.pan3d.DirichletDoublet0Source0Case3(
self._panels, self._trailing_edges)
case.A_ref = self.parametric_glider.shape.area
case.mom_ref_point = self.paraBEM.Vector3(1.25, 0, -6)
case.v_inf = self.paraBEM.Vector(self.parametric_glider.v_inf)
case.drag_calc = 'trefftz'
case.farfield = 5
case.create_wake(10000000, 20)
pols = case.polars(
self.paraBEM_utils.v_inf_deg_range3(case.v_inf, 2, 15, 20))
self.cL = []
self.cDi = []
self.cPi = []
self.alpha = []
for i in pols.values:
self.alpha.append(i.alpha)
self.cL.append(i.cL)
self.cDi.append(i.cD)
self.cPi.append(i.cP)
self.alpha = np.array(self.alpha)
self.cL = np.array(self.cL)
self.cDi = np.array(self.cDi)
self.cPi = np.array(self.cPi)
def min_func(x):
global count
count += 1
print("\niteration: " + str(count))
_glider2d = deepcopy(glider2d)
glider_set_controlpoint(_glider2d, x)
glider3d = _glider2d.get_glider_3d()
panels = paraBEM_Panels(
glider3d,
midribs=0,
profile_numpoints=40,
symmetric=True,
distribution=Distribution.from_nose_cos_distribution(40, 0.2),
num_average=0)
case = Case(panels[1], panels[2])
case.farfield = 5
case.drag_calc = "trefftz"
case.A_ref = 23
case.create_wake(length=10000, count=5)
case.v_inf = paraBEM.Vector3(8, 0, 1)
case.trefftz_cut_pos = case.v_inf * 50
alpha = v_inf_deg_range3(case.v_inf, 5, 9, 20)
polars = case.polars(alpha)
vtk_writer = CaseToVTK(case, "results/vtk_opt", suffix=str(count))
vtk_writer.write_panels(data_type="point")
cL = []
cD = []
for i in polars.values:
cL.append(i.cL)
cD.append(i.cD)
return np.interp(0.6, cL, cD)
def create_panels(self, midribs=0, profile_numpoints=10, mean=False, symmetric=True):
self._vertices, self._panels, self._trailing_edges = paraBEM_Panels(
self.ParametricGlider.get_glider_3d(),
midribs=midribs,
profile_numpoints=profile_numpoints,
num_average=mean*5,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=symmetric)
def setUp(self):
self.glider2d = self.import_glider_2d()
self.glider3d = self.glider2d.get_glider_3d()
config = {"v_inf": [10, 0, 2],
"symmetric_case": True,
"cell_numpoints": 5,
"distribution": Distribution.from_nose_cos_distribution(100, 0.2)
}
self.glidercase = GliderPanelMethod(self.glider3d, config)
def test_glider_mesh(self):
dist = Distribution.from_nose_cos_distribution(30, 0.2)
dist.add_glider_fixed_nodes(self.glider)
self.glider.profile_x_values = dist
m = Mesh(name="glider_mesh")
for cell in self.glider.cells[1:-1]:
m += cell.get_mesh(0)
for rib in self.glider.ribs:
m += Mesh.from_rib(rib)
m.delete_duplicates()
m.get_indexed()
def create_panels(self,
midribs=0,
profile_numpoints=10,
mean=False,
symmetric=True):
self._vertices, self._panels, self._trailing_edges = paraBEM_Panels(
self.parametric_glider.get_glider_3d(),
midribs=midribs,
profile_numpoints=profile_numpoints,
num_average=mean * 5,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=symmetric)
def create_fem_dict(par_glider):
# not yet working
# create a paraBEM object and compute the pressure
# create a dict with:
# nodes, elements, forces, bc, joints
vertices, panels, trailing_edges = paraBEM_Panels(
par_glider.get_glider_3d(),
midribs=0,
profile_numpoints=50,
num_average=4,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=True)
def create_fem_dict(par_glider):
# create a paraBEM object and compute the pressure
# create a dict with:
# nodes, elements, forces, bc, joints
vertices, panels, trailing_edges = paraBEM_Panels(
par_glider.get_glider_3d(),
midribs=0,
profile_numpoints=50,
num_average=4,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=True)
case.A_ref = par_glider.flat_area
case.v_inf = paraBEM.Vector(glider.v_inf)
self.case.farfield = 5
self.case.create_wake(9999, 10)
self.case.run()
def create_fem_dict(par_glider):
# create a paraBEM object and compute the pressure
# create a dict with:
# nodes, elements, forces, bc, joints
vertices, panels, trailing_edges = paraBEM_Panels(
par_glider.get_glider_3d(),
midribs=0,
profile_numpoints=50,
num_average=4,
distribution=Distribution.from_nose_cos_distribution(0.2),
symmetric=True
)
case.A_ref = par_glider.flat_area
case.v_inf = paraBEM.Vector(glider.v_inf)
self.case.farfield = 5
self.case.create_wake(9999, 10)
self.case.run()
def test_run(self):
config = {
"v_inf": [14, 0, 2],
"fem_timestep": 1.e-06,
"fem_steps": 100,
"fem_output": 10,
"d_velocity": 1.,
"pressure_ramp": 100, # steps for linear pressure ramp
"caseType": "line_forces",
"line_numpoints": 10,
"line_rho": 0.00001,
"line_elasticity": 30000,
"rib_rho": 0.00001,
"cell_numpoints": 0,
"vtk_fem_output": "/tmp/Fem/testFEM",
"symmetric_case": True,
"line_numpoints": 2,
"distribution": Distribution.from_nose_cos_distribution(30, 0.3)
}
self.glidercase = GliderFemCase(self.glider3d, config)
self.glidercase.run()
def paraBEM_Panels(glider,
midribs=0,
profile_numpoints=None,
num_average=0,
symmetric=False,
distribution=None):
"""return the vertices, panels and the trailing edge of a glider, as paraBEM objects.
midribs: midribs of a cell spanwise. if num_average is greater then
0 ballooning will be disables
profile_numpoints: coordinates of every rib, choordwise
num_average: steps to average a cell profile
symmetric: set to True if a symmetric result is expected (this will
reduce evaluation time)
"""
# paraBEM is not a dependency of openglider so if problems occure here, get the module.
import paraBEM
if symmetric:
glider = glider.copy()
else:
glider = glider.copy_complete()
glider.close_rib(0)
glider.close_rib()
if profile_numpoints:
glider.profile_x_values = Distribution.from_nose_cos_distribution(
profile_numpoints, 0.2)
if num_average > 0:
glider.apply_mean_ribs(num_average)
glider.close_rib()
ribs = glider.return_ribs(midribs, ballooning=False)
else:
ribs = glider.return_ribs(midribs)
# deleting the last vertex of every rib (no trailing edge gap)
ribs = [rib[:-1] for rib in ribs]
# get a numbered representation + flatten vertices
i = 0
vertices = []
ribs_new = []
panels = []
sym_panels = []
trailing_edge = []
for rib in ribs:
rib_new = []
for vertex in rib:
rib_new.append(i)
vertices.append(vertex)
i += 1
rib_new.append(rib_new[0])
ribs_new.append(rib_new)
ribs = ribs_new
panel_nr = 0
for i, rib_i in enumerate(ribs[:-1]):
rib_j = ribs[i + 1]
if symmetric:
if vertices[rib_j[0]][1] > 0.00001:
trailing_edge.append(rib_i[0])
else:
trailing_edge.append(rib_i[0])
if i == len(ribs[:-2]):
trailing_edge.append(rib_j[0])
for k, _ in enumerate(rib_j[:-1]):
l = k + 1
panel = [rib_i[k], rib_j[k], rib_j[l], rib_i[l]]
if symmetric:
sym = True
add_panel = False
for p in panel:
if not vertices[p][
1] > -0.000001: # if one point lies on the y- side
sym = False # y- is the mirrored side
if not vertices[p][
1] < 0.0001: # if one point lies on the y+ side
add_panel = True
if add_panel:
panels.append(panel)
if sym:
sym_panels.append(panel_nr)
panel_nr += 1
else:
panels.append(panel)
vertices = [paraBEM.PanelVector3(*point) for point in vertices]
panels = [
paraBEM.Panel3([vertices[nr] for nr in panel]) for panel in panels
]
trailing_edge = [vertices[nr] for nr in trailing_edge]
for nr in sym_panels:
panels[nr].set_symmetric()
return vertices, panels, trailing_edge
def profile_numpoints(self, numpoints):
self.profile_x_values = Distribution.from_nose_cos_distribution(numpoints, 0.3)
import paraEigen as eigen import paraBEM.pan2d as bem import paraBEM import paraFEM as fem import matplotlib.tri as mtri import matplotlib.pyplot as plt # parameters numpoints = 80 insert_values = [0.11, 0.27, 0.5, 0.75] # 1: erstelle ein profil dist = Distribution.from_nose_cos_distribution(numpoints, 0.2) dist.insert_values(insert_values) fixed = [list(dist.data).index(value) for value in insert_values] boundary = range(len(dist)) airfoil = Profile2D.compute_trefftz(-0.1, 0.2, 100) airfoil.x_values = dist # 2: berechne druckverteilung (bem) vertices = [paraBEM.PanelVector2(*point) for point in airfoil.data[:-1]] vertices.append(vertices[0]) vertices[0].wake_vertex = True panels = [paraBEM.Panel2(vertices[i:i + 2]) for i in range(len(vertices) - 1)] case = bem.DirichletDoublet0Source0Case2(panels) case.v_inf = eigen.vector2(1, 0.2)
import paraBEM.pan2d as bem import paraBEM import paraFEM as fem import matplotlib.tri as mtri import matplotlib.pyplot as plt # parameters numpoints = 200 insert_values = [0.09, 0.22, 0.5, 0.75] # 1: erstelle ein profil dist = Distribution.from_nose_cos_distribution(numpoints, 0.2) dist.insert_values(insert_values) fixed = [list(dist.data).index(value) for value in insert_values] boundary = range(len(dist)) airfoil = Profile2D.compute_trefftz(m=-0.1+0.1j, tau=0.2, numpoints=100) airfoil.x_values = dist # 2: berechne druckverteilung (bem) vertices = [paraBEM.PanelVector2(*point) for point in airfoil.data[:-1]] vertices.append(vertices[0]) vertices[0].wake_vertex = True panels = [paraBEM.Panel2(vertices[i:i + 2]) for i in range(len(vertices) - 1)] case = bem.DirichletDoublet0Source0Case2(panels) case.v_inf = paraBEM.Vector2(1, 0.1)
