"""Plot the instantaneous force coefficients.""" from matplotlib import pyplot import pathlib import rodney args = rodney.parse_command_line() maindir = pathlib.Path(__file__).absolute().parents[1] # Load force coefficients for simulation with AR=1.27. label = 'AR = 1.27' simudir = maindir / 'Re200_St0.6_AR1.27_psi90' config = rodney.WingKinematics(Re=200, AR=1.27, nt_period=2000) filepath = simudir / 'output' / 'forces-0.txt' solution = rodney.load_force_coefficients(filepath, config) rodney.print_stats(label, *rodney.get_stats(solution, limits=(4, 5))) plot_kwargs = dict(color='C3', linestyle='-') # Load force coefficients for simulation with AR=1.91. label2 = 'AR = 1.91' simudir2 = maindir / 'Re200_St0.6_AR1.91_psi90' config2 = rodney.WingKinematics(Re=200, AR=1.91, nt_period=2000) filepath = simudir2 / 'output' / 'forces-0.txt' solution2 = rodney.load_force_coefficients(filepath, config2) rodney.print_stats(label2, *rodney.get_stats(solution2, limits=(4, 5))) plot_kwargs2 = dict(color='black', linestyle='--') # Load force coefficients for simulation with AR=2.55. label3 = 'AR = 2.55' simudir3 = maindir / 'Re200_St0.6_AR2.55_psi90'
"""Plot the instantaneous force coefficients.""" from matplotlib import pyplot import pathlib import rodney args = rodney.parse_command_line() maindir = pathlib.Path(__file__).absolute().parents[1] # Load force coefficients for simulation with psi=90. label = r'$\psi = 90^o$' simudir = maindir / 'Re200_St0.6_AR1.27_psi90' config = rodney.WingKinematics(psi=90.0) filepath = simudir / 'output' / 'forces-0.txt' solution = rodney.load_force_coefficients(filepath, config) rodney.print_stats(label, *rodney.get_stats(solution, limits=(4, 5))) plot_kwargs = dict(color='C3', linestyle='-') # Load force coefficients for simulation with psi=100. label2 = r'$\psi = 100^o$' simudir2 = maindir / 'Re200_St0.6_AR1.27_psi100' config2 = rodney.WingKinematics(psi=100.0) filepath = simudir2 / 'output' / 'forces-0.txt' solution2 = rodney.load_force_coefficients(filepath, config2) rodney.print_stats(label2, *rodney.get_stats(solution2, limits=(4, 5))) plot_kwargs2 = dict(color='C2', linestyle='--') # Load force coefficients for simulation with psi=110. label3 = r'$\psi = 110^o$' simudir3 = maindir / 'Re200_St0.6_AR1.27_psi110'
from collections import OrderedDict
import numpy
import pathlib
import yaml
import petibmpy
import rodney
# Set the simulation directory.
simudir = pathlib.Path(__file__).absolute().parents[1]
datadir = simudir / 'output'
# Set the wing kinematics.
config = rodney.WingKinematics(nt_period=2000)
c = config.c # chord length
S = config.S # spanwise length
A_phi = config.A_phi # rolling amplitude (radians)
n_periods = config.n_periods # number of flapping cycles
nt_period = config.nt_period # number of time steps per cycle
dt = config.dt # time-step size
probes = [] # will store info about the probes
# Set probe information for the x- and y- components of the velocity.
fields = ['u', 'v']
for field in fields:
filepath = datadir / 'grid.h5'
grid = petibmpy.read_grid_hdf5(filepath, field)
xlocs = [1.0, 2.0, 3.0, 4.0, 5.0]
def resize_for_uniform(L, xc, dx, buf=0.0):
"""Adjust the limits of the interval to allow uniform discretization."""
xs, xe = xc - L / 2 - buf, xc + L / 2 + buf
L = xe - xs
n = math.ceil(L / dx)
L = n * dx
xs, xe = xc - L / 2, xc + L / 2
assert abs((xe - xs) / n - dx) < 1e-12
return xs, xe
Box = collections.namedtuple(
'Box', ['xstart', 'xend', 'ystart', 'yend', 'zstart', 'zend'])
config = rodney.WingKinematics(psi=70.0, Re=200, St=0.6, nt_period=2000)
c, S, A_phi = config.c, config.S, config.A_phi
box1 = Box(-15.0, 15.0, -12.5, 12.5, -12.5, 12.5)
box2, width2 = Box(-2.0, 6.0, -3.0, 3.0, -1.0, 2.0), 0.05 * c
dx = 0.01 * c
buf = 0.05 * c
xs, xe = resize_for_uniform(c, 0.0, dx, buf=buf)
ys, ye = resize_for_uniform(2 * S * numpy.cos(A_phi), 0.0, dx, buf=buf)
zs, ze = resize_for_uniform(S, S / 2, dx, buf=buf)
box3, width3 = Box(xs, xe, ys, ye, zs, ze), dx
show_figure = False
config_x = get_gridline_config(box1.xstart, box2.xstart, box3.xstart,
"""Plot the instantaneous force coefficients and compare grid resolutions."""
from matplotlib import pyplot
import pathlib
import rodney
args = rodney.parse_command_line()
maindir = pathlib.Path(__file__).absolute().parents[1]
data = {}
# Process force coefficients for simulation on coarse mesh.
label = 'Coarse'
simudir = maindir / 'run1'
config = rodney.WingKinematics(Re=200.0, St=0.6, psi=90.0, nt_period=2000)
filepath = simudir / 'output' / 'forces-0.txt'
solution = rodney.load_force_coefficients(filepath, config)
rodney.print_stats(label, *rodney.get_stats(solution, limits=(4, 5)))
data[label] = dict(config=config,
solution=solution,
plot_kwargs=dict(linestyle='-', color='C0'))
# Process force coefficients for simulation on intermediate mesh.
label = 'Nominal'
simudir = maindir / 'run3'
config = rodney.WingKinematics(Re=200.0, St=0.6, psi=90.0, nt_period=2000)
filepath = simudir / 'output' / 'forces-0.txt'
solution = rodney.load_force_coefficients(filepath, config)
rodney.print_stats(label, *rodney.get_stats(solution, limits=(4, 5)))
data[label] = dict(config=config,
solution=solution,
simudir = pathlib.Path(__file__).absolute().parents[1]
datadir = simudir / 'output'
# Compute the cycle-averaged thrust coefficient.
filepath = datadir / 'forces-0.txt'
t, fx, _, _ = petibmpy.read_forces(filepath)
thrust = -fx # switch from drag to thrust
time_limits = (4 * T, 5 * T) # interval to consider for average
thrust_avg, = petibmpy.get_time_averaged_values(t, thrust, limits=time_limits)
# Create the wing kinematics.
wing = rodney.WingKinematics(c=1.0,
AR=1.27,
hook=(0.0, 0.0, 0.0),
A_phi=45.0,
A_theta=45.0,
psi=90.0,
theta_bias=0.0,
Re=200.0,
U_inf=1.0,
St=0.6)
# Load original boundary coordinates from file.
filepath = simudir / 'wing.body'
wing.load_body(filepath, skiprows=1)
x0, y0, z0 = wing.get_coordinates()
# Grab 3 reference points (to later compute unit normal vector).
points0 = Point(x0[:3], y0[:3], z0[:3])
dx = 0.01 # grid-spacing size in the vicinity of the body
ds = dx**2 # surface area associated with each marker
"""Plot the instantaneous force coefficients."""
from matplotlib import pyplot
import numpy
import pathlib
import rodney
args = rodney.parse_command_line()
maindir = pathlib.Path(__file__).absolute().parents[1]
# Load force coefficients for simulation at Re=100.
label = 'Re = 100'
simudir = maindir / 'Re100_St0.6_AR1.27_psi90'
config = rodney.WingKinematics(Re=100, nt_period=2000)
filepath = simudir / 'output' / 'forces-0.txt'
solution = rodney.load_force_coefficients(filepath, config)
rodney.print_stats(label, *rodney.get_stats(solution, limits=(4, 5)))
mask = numpy.where((solution.t >= 4) & (solution.t <= 5))[0]
print('max(|C_T|) =', numpy.max(numpy.abs(solution.ct[mask])))
plot_kwargs = dict(color='black', linestyle='--')
# Load force coefficients for simulation at Re=200.
label2 = 'Re = 200'
simudir2 = maindir / 'Re200_St0.6_AR1.27_psi90'
config2 = rodney.WingKinematics(Re=200, nt_period=2000)
filepath = simudir2 / 'output' / 'forces-0.txt'
solution2 = rodney.load_force_coefficients(filepath, config2)
rodney.print_stats(label2, *rodney.get_stats(solution2, limits=(4, 5)))
mask = numpy.where((solution2.t >= 4) & (solution2.t <= 5))[0]
"""Write the YAML configuration file for the probes."""
import numpy
import pathlib
import yaml
import petibmpy
import rodney
# Set the simulation directory.
simudir = pathlib.Path(__file__).absolute().parents[1]
datadir = simudir / 'output'
# Set the kinematics of the wing.
config = rodney.WingKinematics(AR=1.91, Re=200, St=0.6, nt_period=2000)
c, S, A_phi = config.c, config.S, config.A_phi
n_periods, nt_period = config.n_periods, config.nt_period
dt = config.dt
probes = [] # will store info about the probes
# Set probe information for the x- and y- components of the velocity.
fields = ['u', 'v']
for field in fields:
filepath = datadir / 'grid.h5'
grid = petibmpy.read_grid_hdf5(filepath, field)
xlocs = [1.0, 2.0, 3.0, 4.0, 5.0]
for i, xloc in enumerate(xlocs):
name = f'probe{i + 1}-{field}'
"""Print parameters related to the kinematics of the wing.""" import numpy import rodney kinematics = rodney.WingKinematics(psi=80.0, Re=200, St=0.6, nt_period=2000) print(kinematics)
args = rodney.parse_command_line()
maindir = pathlib.Path(__file__).parents[1]
datadir = maindir / 'output'
# Load gridline coordinates from file.
filepath = datadir / 'grid.h5'
x, y, z = petibmpy.read_grid_hdf5(filepath, 'vertex')
# Subset gridline coordinates.
x, xlim = subset_gridline(x, -5.0, 5.0)
y, ylim = subset_gridline(y, -5.0, 5.0)
z, zlim = subset_gridline(z, -5.0, 5.0)
# Load body coordinates from file.
filepath = maindir / 'wing.body'
wing = rodney.WingKinematics()
wing.load_body(filepath, skiprows=1)
# Keep only points on the contour of the wing.
x0, _, z0 = wing.get_coordinates(org=True)
points = numpy.array([x0, z0]).T
hull = ConvexHull(points)
x0, z0 = points[hull.vertices, 0], points[hull.vertices, 1]
y0 = numpy.zeros_like(x0)
wing.set_coordinates(x0, y0, z0, org=True)
# Get position at given time.
xb, yb, zb = wing.compute_position(0.0)
pyplot.rc('font', family='serif', size=12)
"""Print parameters related to the kinematics of the wing.""" import numpy import rodney kinematics = rodney.WingKinematics(nt_period=1000) print(kinematics)
roll=phi, pitch=theta,
center=wing.hook)
p1, p2, p3 = numpy.array([x, y, z]).T
v1 = (p1 - p2) / numpy.linalg.norm(p1 - p2)
v2 = (p3 - p1) / numpy.linalg.norm(p3 - p1)
v3 = numpy.cross(v1, v2)
return v3 / numpy.linalg.norm(v3)
# Set simulation directory and data directory.
simudir = pathlib.Path(__file__).absolute().parents[1]
datadir = simudir / 'output'
# Create the wing kinematics.
wing = rodney.WingKinematics(Re=200.0, St=0.6, psi=110.0, nt_period=2000)
# Compute the cycle-averaged thrust.
filepath = datadir / 'forces-0.txt'
t, fx, _, _ = petibmpy.read_forces(filepath)
thrust = -fx # switch from drag to thrust
time_limits = (4 * wing.T, 5 * wing.T) # interval to consider for average
thrust_avg, = petibmpy.get_time_averaged_values(t, thrust, limits=time_limits)
# Compute the cycle-averaged thrust coefficient.
rho, U_inf, A_plan = (getattr(wing, name)
for name in ('rho', 'U_inf', 'A_plan'))
scale = 1 / (0.5 * rho * U_inf**2 * A_plan)
ct, = petibmpy.get_force_coefficients(thrust, coeff=scale)
ct_avg, = petibmpy.get_time_averaged_values(t, ct, limits=time_limits)
pitch=theta,
center=wing.hook)
p1, p2, p3 = numpy.array([x, y, z]).T
v1 = (p1 - p2) / numpy.linalg.norm(p1 - p2)
v2 = (p3 - p1) / numpy.linalg.norm(p3 - p1)
v3 = numpy.cross(v1, v2)
return v3 / numpy.linalg.norm(v3)
# Set simulation directory and data directory.
simudir = pathlib.Path(__file__).absolute().parents[1]
datadir = simudir / 'output'
# Create the wing kinematics.
wing = rodney.WingKinematics(Re=200.0, St=1.0, nt_period=2000)
# Compute the cycle-averaged thrust.
filepath = datadir / 'forces-0.txt'
t, fx, _, _ = petibmpy.read_forces(filepath)
thrust = -fx # switch from drag to thrust
time_limits = (4 * wing.T, 5 * wing.T) # interval to consider for average
thrust_avg, = petibmpy.get_time_averaged_values(t, thrust, limits=time_limits)
# Compute the cycle-averaged thrust coefficient.
rho, U_inf, A_plan = (getattr(wing, name)
for name in ('rho', 'U_inf', 'A_plan'))
scale = 1 / (0.5 * rho * U_inf**2 * A_plan)
ct, = petibmpy.get_force_coefficients(thrust, coeff=scale)
ct_avg, = petibmpy.get_time_averaged_values(t, ct, limits=time_limits)
"""Print parameters related to the kinematics of the wing.""" import numpy import rodney kinematics = rodney.WingKinematics(AR=2.55, Re=200, St=0.6, nt_period=2000) print(kinematics)
"""Create the body and write the coordinates to a file.""" import pathlib import petibmpy import rodney # Set the simulation directory. simudir = pathlib.Path(__file__).absolute().parents[1] # Create the configuration for the wing kinematics. wing = rodney.WingKinematics(Re=200, St=0.6, nt_period=2000) # Discretize the body. wing.create_body(ds=0.01, sort_points=True) x, y, z = wing.get_coordinates() # Save the coordinates into a file. filepath = simudir / 'wing.body' petibmpy.write_body(filepath, x, y, z)
def resize_for_uniform(L, xc, dx, buf=0.0):
"""Adjust the limits of the interval to allow uniform discretization."""
xs, xe = xc - L / 2 - buf, xc + L / 2 + buf
L = xe - xs
n = math.ceil(L / dx)
L = n * dx
xs, xe = xc - L / 2, xc + L / 2
assert abs((xe - xs) / n - dx) < 1e-12
return xs, xe
Box = collections.namedtuple('Box', ['xstart', 'xend',
'ystart', 'yend',
'zstart', 'zend'])
config = rodney.WingKinematics(Re=200, St=0.8, nt_period=2000)
c, S, A_phi = config.c, config.S, config.A_phi
box1 = Box(-15.0, 15.0, -12.5, 12.5, -12.5, 12.5)
box2, width2 = Box(-2.0, 6.0, -3.0, 3.0, -1.0, 2.0), 0.05 * c
dx = 0.01 * c
buf = 0.05 * c
xs, xe = resize_for_uniform(c, 0.0, dx, buf=buf)
ys, ye = resize_for_uniform(2 * S * numpy.cos(A_phi), 0.0, dx, buf=buf)
zs, ze = resize_for_uniform(S, S / 2, dx, buf=buf)
box3, width3 = Box(xs, xe, ys, ye, zs, ze), dx
show_figure = False
config_x = get_gridline_config(box1.xstart, box2.xstart, box3.xstart,
Slice the spanwise vorticity in the x/y plane at the midspan (z=S/2).
"""
import collections
from matplotlib import pyplot, patches
import numpy
import pathlib
import petibmpy
import rodney
# Parse command line, and set kinematics and directories.
args = rodney.parse_command_line()
config = rodney.WingKinematics(Re=200, St=0.6, AR=1.27, nt_period=2000)
simudir = pathlib.Path(__file__).absolute().parents[1]
datadir = simudir / 'output'
# Set parameters.
t_nodim = 4.25 # non-dimensional time
t = t_nodim * config.T # time
timestep = int(t / config.dt) # time-step index
theta = config.pitching(t) # pitching angle (radians)
if args.save_figures:
# Create directory for figures if needed.
figdir = simudir / 'figures'
figdir.mkdir(parents=True, exist_ok=True)
# Set default font family and size for Matplotlib figures.
"""Print parameters related to the kinematics of the wing.""" import numpy import rodney kinematics = rodney.WingKinematics(Re=200, St=0.4, nt_period=2000) print(kinematics)
