def plot_flap(x, y, x_J, theta, image):
"""
Plot flap with actuators. theta is clockwise positive.
@Author: Endryws (modified by Pedro Leal)
Created on Fri Mar 18 14:26:54 2016
"""
x_dict, y_dict = af.separate_upper_lower(x, y)
# Below I create the dictionarys used to pass to the function find_hinge
upper = {'x': x_dict['upper'], 'y': y_dict['upper']} # x and y upper points
lower = {'x': x_dict['lower'], 'y': y_dict['lower']} # x and y lower points
hinge = af.find_hinge(x_J, upper, lower)
#=======================================================================
# With the Joint (hinge) point, i can use the find flap function to
# found the points of the flap in the airfoil.
#=======================================================================
data = {'x': x, 'y': y}
static_data, flap_data = af.find_flap(data, hinge)
R = hinge['y_upper']
theta_list = np.linspace(3*math.pi/2, math.pi/2, 50)
x_circle_list = hinge['x'] + R*np.cos(theta_list)
y_circle_list = hinge['y'] + R*np.sin(theta_list)
n_upper = len(flap_data['x'])/2
# Ploting the flap in the original position
# plt.plot(flap_data['x'][:n_upper],flap_data['y'][:n_upper],'k--')
# plt.plot(flap_data['x'][n_upper:],flap_data['y'][n_upper:],'k--')
# Rotate and plot
upper = {'x': np.concatenate((flap_data['x'][:n_upper], x_circle_list)),
'y': np.concatenate((flap_data['y'][:n_upper], y_circle_list))}
lower = {'x':(flap_data['x'][n_upper:]),
'y':(flap_data['y'][n_upper:])}
rotated_upper, rotated_lower = af.rotate(upper, lower, hinge, theta,
unit_theta = 'rad')
image2 = plt.plot(static_data['x'], static_data['y'],'k')
image3 = plt.plot(rotated_upper['x'], rotated_upper['y'],'k')
image4 = plt.plot(rotated_lower['x'], rotated_lower['y'],'k')
image += image2 + image3 + image4
return image
def plot_flap(x, y, x_J, y_J = None, theta = 0):
"""
Plot flap with actuators. theta is clockwise positive.
@Author: Endryws (modified by Pedro Leal)
Created on Fri Mar 18 14:26:54 2016
"""
import matplotlib.pyplot as plt
plt.figure()
x_dict, y_dict = af.separate_upper_lower(x, y)
# Below I create the dictionarys used to pass to the function find_hinge
upper = {'x': x_dict['upper'], 'y': y_dict['upper']} # x and y upper points
lower = {'x': x_dict['lower'], 'y': y_dict['lower']} # x and y lower points
hinge = af.find_hinge(x_J, upper, lower)
#=======================================================================
# With the Joint (hinge) point, i can use the find flap function to
# found the points of the flap in the airfoil.
#=======================================================================
data = {'x': x, 'y': y}
static_data, flap_data = af.find_flap(data, hinge)
R = hinge['y_upper']
theta_list = np.linspace(3*math.pi/2, math.pi/2, 50)
x_circle_list = hinge['x'] + R*np.cos(theta_list)
y_circle_list = hinge['y'] + R*np.sin(theta_list)
n_upper = len(flap_data['x'])/2
# Ploting the flap in the original position
plt.plot(flap_data['x'][:n_upper],flap_data['y'][:n_upper],'k--')
plt.plot(flap_data['x'][n_upper:],flap_data['y'][n_upper:],'k--')
# Rotate and plot
upper = {'x': np.concatenate((flap_data['x'][:n_upper], x_circle_list)),
'y': np.concatenate((flap_data['y'][:n_upper], y_circle_list))}
lower = {'x':(flap_data['x'][n_upper:]),
'y':(flap_data['y'][n_upper:])}
rotated_upper, rotated_lower = af.rotate(upper, lower, hinge, theta,
unit_theta = 'rad')
plt.plot(static_data['x'], static_data['y'],'k')
plt.plot(rotated_upper['x'], rotated_upper['y'],'k')
plt.plot(rotated_lower['x'], rotated_lower['y'],'k')
plt.axes().set_aspect('equal')
l.plot_actuator()
s.plot_actuator()
if y_J != None:
for i in range(y_J):
plt.scatter(x_J , y_J[i])
plt.grid()
plt.locator_params(axis = 'y', nbins=6)
plt.xlabel('${}_{I}x + x_J$')
plt.ylabel('${}_{I}y$')
border = 0.05
plt.xlim(-border, 1+border)
plt.savefig( str(np.floor(100*abs(theta))) + "_configuration.png")
plt.close()
def calculate_flap_moment(x, y, alpha, x_hinge, deflection):
"""For a given airfoil with coordinates x and y at angle of attack
alpha, calculate the moment coefficient around the joint at x_hinge
and deflection """
def separate_upper_lower(x, y, Cp = None, i_separator=None):
"""Return dictionaries with upper and lower keys with respective
coordiantes. It is assumed the leading edge is frontmost point at
alpha=0"""
#TODO: when using list generated by xfoil, there are two points for
#the leading edge
def separate(variable_list, i_separator):
if type(i_separator) == int:
variable_dictionary = {'upper': variable_list[0:i_separator+1],
'lower': variable_list[i_separator+1:]}
elif type(i_separator) == list:
i_upper = i_separator[0]
i_lower = i_separator[1]
variable_dictionary = {'upper': variable_list[0:i_upper],
'lower': variable_list[i_lower:]}
return variable_dictionary
#If i is not defined, separate upper and lower surface from the
# leading edge
if i_separator == None:
i_separator = x.index(min(x))
if Cp == None:
x = separate(x, i_separator)
y = separate(y, i_separator)
return x, y
else:
x = separate(x, i_separator)
y = separate(y, i_separator)
Cp = separate(Cp, i_separator)
return x, y, Cp
# If x and y are not dictionaries with keys upper and lower, make them
# be so
if type(x) == list:
x, y = separate_upper_lower(x, y)
upper = {'x': x['upper'], 'y': y['upper']}
lower = {'x': x['lower'], 'y': y['lower']}
#Determining hinge
hinge = af.find_hinge(x_hinge, upper, lower)
upper_static, upper_flap = af.find_flap(upper, hinge)
lower_static, lower_flap = af.find_flap(lower, hinge, lower = True)
upper_rotated, lower_rotated = af.rotate(upper_flap, lower_flap, hinge, deflection)
flapped_airfoil, i_separator = af.clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5,
return_flap_i = True)
#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
#Third step: get new values of pressure coefficient
xf.create_input(x = flapped_airfoil['x'], y_u = flapped_airfoil['y'],
filename = 'flapped', different_x_upper_lower = True)
Data = xf.find_pressure_coefficients('flapped', alpha, NACA = False)
x, y, Cp = separate_upper_lower(x = Data['x'], y = Data['y'],
Cp = Data['Cp'], i_separator = i_separator)
Cm = ar.calculate_moment_coefficient(x, y, Cp, alpha = alpha, c = 1.,
x_ref = x_hinge, y_ref = 0.)
print Cm
def calculate_flap_moment(x, y, alpha, x_hinge, deflection,
unit_deflection = 'rad'):
"""For a given airfoil with coordinates x and y at angle of attack
alpha (degrees), calculate the moment coefficient around the joint at x_hinge
and deflection in radians (unit_deflection = 'rad') or degrees
(unit_deflection = 'deg')"""
# If x and y are not dictionaries with keys upper and lower, make them
# be so
if type(x) == list:
x, y = af.separate_upper_lower(x, y)
#Because parts of the program use keys 'u' and 'l', and other parts use
#'upper' and 'lower'
if 'u' in x.keys():
upper = {'x': x['u'], 'y': y['u']}
lower = {'x': x['l'], 'y': y['l']}
elif 'upper' in x.keys():
upper = {'x': x['upper'], 'y': y['upper']}
lower = {'x': x['lower'], 'y': y['lower']}
hinge = af.find_hinge(x_hinge, upper, lower)
if deflection > 0:
upper_static, upper_flap = af.find_flap(upper, hinge)
lower_static, lower_flap = af.find_flap(lower, hinge,
extra_points = 'lower')
elif deflection < 0:
upper_static, upper_flap = af.find_flap(upper, hinge,
extra_points = 'upper')
lower_static, lower_flap = af.find_flap(lower, hinge)
else:
upper_static, upper_flap = af.find_flap(upper, hinge,
extra_points = None)
lower_static, lower_flap = af.find_flap(lower, hinge,
extra_points = None)
upper_rotated, lower_rotated = af.rotate(upper_flap, lower_flap,
hinge, deflection,
unit_theta = unit_deflection)
flapped_airfoil, i_separator = af.clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = None,
return_flap_i = True)
#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
#Third step: get new values of pressure coefficient
xf.create_input(x = flapped_airfoil['x'], y_u = flapped_airfoil['y'],
filename = 'flapped', different_x_upper_lower = True)
Data = xf.find_pressure_coefficients('flapped', alpha, NACA = False)
x, y, Cp = af.separate_upper_lower(x = Data['x'], y = Data['y'],
Cp = Data['Cp'], i_separator = i_separator)
#At the hinges, the reaction moment has the opposite sign of the
#actuated torque
Cm = - ar.calculate_moment_coefficient(x, y, Cp, alpha = alpha, c = 1.,
x_ref = x_hinge, y_ref = 0.,
flap = True)
return Cm
def calculate_flap_moment(x,
y,
alpha,
x_hinge,
deflection,
unit_deflection='rad'):
"""For a given airfoil with coordinates x and y at angle of attack
alpha (degrees), calculate the moment coefficient around the joint at x_hinge
and deflection in radians (unit_deflection = 'rad') or degrees
(unit_deflection = 'deg')"""
# If x and y are not dictionaries with keys upper and lower, make them
# be so
if type(x) == list:
x, y = af.separate_upper_lower(x, y)
#Because parts of the program use keys 'u' and 'l', and other parts use
#'upper' and 'lower'
if 'u' in x.keys():
upper = {'x': x['u'], 'y': y['u']}
lower = {'x': x['l'], 'y': y['l']}
elif 'upper' in x.keys():
upper = {'x': x['upper'], 'y': y['upper']}
lower = {'x': x['lower'], 'y': y['lower']}
hinge = af.find_hinge(x_hinge, upper, lower)
if deflection > 0:
upper_static, upper_flap = af.find_flap(upper, hinge)
lower_static, lower_flap = af.find_flap(lower,
hinge,
extra_points='lower')
elif deflection < 0:
upper_static, upper_flap = af.find_flap(upper,
hinge,
extra_points='upper')
lower_static, lower_flap = af.find_flap(lower, hinge)
else:
upper_static, upper_flap = af.find_flap(upper,
hinge,
extra_points=None)
lower_static, lower_flap = af.find_flap(lower,
hinge,
extra_points=None)
upper_rotated, lower_rotated = af.rotate(upper_flap,
lower_flap,
hinge,
deflection,
unit_theta=unit_deflection)
flapped_airfoil, i_separator = af.clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=None,
return_flap_i=True)
#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
#Third step: get new values of pressure coefficient
xf.create_input(x=flapped_airfoil['x'],
y_u=flapped_airfoil['y'],
filename='flapped',
different_x_upper_lower=True)
Data = xf.find_pressure_coefficients('flapped', alpha, NACA=False)
x, y, Cp = af.separate_upper_lower(x=Data['x'],
y=Data['y'],
Cp=Data['Cp'],
i_separator=i_separator)
#At the hinges, the reaction moment has the opposite sign of the
#actuated torque
Cm = -ar.calculate_moment_coefficient(
x, y, Cp, alpha=alpha, c=1., x_ref=x_hinge, y_ref=0., flap=True)
return Cm
def calculate_flap_coefficients(
x,
y,
alpha,
x_hinge,
deflection,
Reynolds=0,
):
"""For a given airfoil with coordinates x and y at angle of attack
alpha, calculate the moment coefficient around the joint at x_hinge
and deflection """
def separate_upper_lower(x, y, Cp=None, i_separator=None):
"""Return dictionaries with upper and lower keys with respective
coordiantes. It is assumed the leading edge is frontmost point at
alpha=0"""
#TODO: when using list generated by xfoil, there are two points for
#the leading edge
def separate(variable_list, i_separator):
if type(i_separator) == int:
variable_dictionary = {
'upper': variable_list[0:i_separator + 1],
'lower': variable_list[i_separator + 1:]
}
elif type(i_separator) == list:
i_upper = i_separator[0]
i_lower = i_separator[1]
variable_dictionary = {
'upper': variable_list[0:i_upper],
'lower': variable_list[i_lower:]
}
return variable_dictionary
#If i is not defined, separate upper and lower surface from the
# leading edge
if i_separator == None:
i_separator = x.index(min(x))
if Cp == None:
x = separate(x, i_separator)
y = separate(y, i_separator)
return x, y
else:
x = separate(x, i_separator)
y = separate(y, i_separator)
Cp = separate(Cp, i_separator)
return x, y, Cp
# If x and y are not dictionaries with keys upper and lower, make them
# be so
if type(x) == list:
x, y = separate_upper_lower(x, y)
upper = {'x': x['upper'], 'y': y['upper']}
lower = {'x': x['lower'], 'y': y['lower']}
#Determining hinge
hinge = af.find_hinge(x_hinge, upper, lower)
upper_static, upper_flap = af.find_flap(upper, hinge)
lower_static, lower_flap = af.find_flap(lower, hinge, lower=True)
upper_rotated, lower_rotated = af.rotate(upper_flap, lower_flap, hinge,
deflection)
flapped_airfoil, i_separator = af.clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5,
return_flap_i=True)
#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
#Third step: get new values of pressure coefficient
xf.create_input(x=flapped_airfoil['x'],
y_u=flapped_airfoil['y'],
filename='flapped',
different_x_upper_lower=True)
Data = xf.find_coefficients('flapped',
alpha,
NACA=False,
Reynolds=Reynolds,
iteration=500)
return Data
