def update_aero_prop(self):
assert hasattr(self,'conn_glob'),\
'Run "update_derived_params" before generating files'
n_surfaces = self.n_surfaces
num_node_surf = self.num_node_surf
num_node_tot = self.num_node_tot
num_elem_surf = self.num_elem_surf
num_elem_tot = self.num_elem_tot
### Generate aerofoil profiles. Only on surf 0.
Airfoils_surf = []
if n_surfaces == 2:
for inode in range(num_node_surf):
eta = inode / num_node_surf
Airfoils_surf.append(
np.column_stack(
geo_utils.interpolate_naca_camber(
eta, self.root_airfoil_M, self.root_airfoil_P,
self.tip_airfoil_M, self.tip_airfoil_P)))
airfoil_distribution_surf = self.conn_surf
airfoil_distribution = np.concatenate([
airfoil_distribution_surf, airfoil_distribution_surf[::-1,
[1, 0, 2]]
])
if n_surfaces == 1:
num_node_half = (num_node_surf + 1) // 2
for inode in range(num_node_half):
eta = inode / num_node_half
Airfoils_surf.append(
np.column_stack(
geo_utils.interpolate_naca_camber(
eta, self.root_airfoil_M, self.root_airfoil_P,
self.tip_airfoil_M, self.tip_airfoil_P)))
airfoil_distribution_surf = self.conn_surf[:num_elem_surf // 2, :]
airfoil_distribution = np.concatenate([
airfoil_distribution_surf[::-1, [1, 0, 2]],
airfoil_distribution_surf
])
self.Airfoils_surf = Airfoils_surf
self.airfoil_distribution = airfoil_distribution
### others
self.aero_node = np.ones((num_node_tot, ), dtype=bool)
self.surface_m = self.M * np.ones((n_surfaces, ), dtype=int)
self.twist = np.zeros((num_elem_tot, 3))
self.chord = self.main_chord * np.ones((num_elem_tot, 3))
self.elastic_axis = self.main_ea * np.ones((
num_elem_tot,
3,
))
def interpolate_naca_camber(eta, M00, P00, M01, P01):
"""
Warnings:
This function is now located in sharpy.utils.geo_utils
Interpolate aerofoil camber at non-dimensional coordinate eta in (0,1),
where (M00,P00) and (M01,P01) define the camber properties at eta=0 and
eta=1 respectively.
Notes:
For two surfaces, eta can be in (-1,1). In this case, the root is eta=0
and the tips are at eta=+-1.
"""
warnings.warn(
'Deprecated utility function location. Use the one in sharpy.utils.geo_utils instead',
stacklevel=2)
x_vec, y_vec = new_geo_utils.interpolate_naca_camber(
eta, M00, P00, M01, P01)
# # define domain
# eta = np.abs(eta)
# assert np.max(eta) < 1. + 1e-16, 'eta exceeding +/- 1!'
#
# # define reference
# x00, y00 = generate_naca_camber(M00, P00)
# x01, y01 = generate_naca_camber(M01, P01)
#
# # interpolate
# x_vec = x00 * (1. - eta) + x01 * eta
# y_vec = y00 * (1. - eta) + y01 * eta
return x_vec, y_vec
def update_aero_prop(self):
assert hasattr(self, 'conn_glob'), \
'Run "update_derived_params" before generating files'
n_surfaces = self.n_surfaces
num_node_surf = self.num_node_surf
num_node_tot = self.num_node_tot
num_elem_surf = self.num_elem_surf
num_elem_tot = self.num_elem_tot
pct_flap = self.pct_flap
control_surface = self.control_surface
### Generate aerofoil profiles. Only on surf 0.
Airfoils_surf = []
if n_surfaces == 2:
for inode in range(num_node_surf):
eta = inode / num_node_surf
Airfoils_surf.append(
np.column_stack(
geo_utils.interpolate_naca_camber(
eta,
self.root_airfoil_M, self.root_airfoil_P,
self.tip_airfoil_M, self.tip_airfoil_P)))
# if inode >= num_node_surf // 2:
ws_elem = 0
for i_surf in range(2):
print('Surface' + str(i_surf))
for i_elem in range(num_elem_surf):
for i_local_node in range(self.num_node_elem):
if i_elem >= int(num_elem_surf *(1- pct_flap)):
if i_surf == 0:
control_surface[ws_elem + i_elem, i_local_node] = 0 # Right flap
else:
control_surface[ws_elem + i_elem, i_local_node] = 0 # Left flap
ws_elem += num_elem_surf
# control_surface[i_elem, i_local_node] = 0
airfoil_distribution_surf = self.conn_surf
airfoil_distribution = np.concatenate([airfoil_distribution_surf,
airfoil_distribution_surf[::-1, [1, 0, 2]]])
control_surface[-num_elem_surf:] = control_surface[-num_elem_surf:, :][::-1]
if n_surfaces == 1:
num_node_half = (num_node_surf + 1) // 2
for inode in range(num_node_half):
eta = inode / num_node_half
Airfoils_surf.append(
np.column_stack(
geo_utils.interpolate_naca_camber(
eta,
self.root_airfoil_M, self.root_airfoil_P,
self.tip_airfoil_M, self.tip_airfoil_P)))
airfoil_distribution_surf = self.conn_surf[:num_elem_surf // 2, :]
airfoil_distribution = np.concatenate([
airfoil_distribution_surf[::-1, [1, 0, 2]],
airfoil_distribution_surf])
self.Airfoils_surf = Airfoils_surf
self.airfoil_distribution = airfoil_distribution
### others
self.aero_node = np.ones((num_node_tot,), dtype=bool)
self.surface_m = self.M * np.ones((n_surfaces,), dtype=int)
self.twist = np.zeros((num_elem_tot, 3))
self.chord = self.main_chord * np.ones((num_elem_tot, 3))
self.elastic_axis = self.main_ea * np.ones((num_elem_tot, 3,))
self.control_surface = control_surface