def find_deflection(x_hinge,
upper_cruise,
lower_cruise,
type='Match trailing edge',
alpha=0,
Reynolds=0,
**kwargs):
"""
Function to calculate the flap deflection.
Required inputs:
:param x_hinge
:param upper_cruise
:param lower_cruise
:param type: can be:
- 'Match trailing edge': will find the deflection where the
baseline's trailing edge matches that of the objective, i.e.
match the the trailing edge of a traditional flap with a
morphing conitunous flap.
- 'Same Cl': will find deflection where Cl of flapped airfoil
is equal to the the objective airfoil.
- 'Range of deflection'
kwrgs arguments for 'Match trailing edge':
:param x_TE_objective
:param y_TE_objective
:param x_TE_baseline
:param y_TE_baseline
kwrgs arguments for 'Same Cl':
:param Cl_objective
kwrgs arguments for 'Same Cd':
:param Cd_objective
kwrgs arguments for 'Range of deflection'
:param max_deflection
Optional arguments:
:param alpha
:param Reynolds
"""
import xfoil_module as xf
airfoil = 'flapped_airfoil'
if type == 'Match trailing edge':
x_TE_objective = kwargs['x_TE_objective']
y_TE_objective = kwargs['y_TE_objective']
x_TE_baseline = kwargs['x_TE_baseline']
y_TE_baseline = kwargs['y_TE_baseline']
elif type == 'Same Cl':
Cl_objective = kwargs['Cl_objective']
elif type == 'Same Cd':
Cd_objective = kwargs['Cd_objective']
elif type == 'Range of deflection':
max_deflection = kwargs['max_deflection']
init_deflection = kwargs['init_deflection']
step = kwargs['step']
hinge = find_hinge(x_hinge, upper_cruise, lower_cruise)
upper_static, upper_flap = find_flap(upper_cruise, hinge)
lower_static, lower_flap = find_flap(lower_cruise, hinge)
#==============================================================================
# Find Deflection
#==============================================================================
if type == 'Match trailing edge':
#Calculate deflection angle in radians
deflection = np.arctan2(hinge['y'] - y_TE_objective,
x_TE_objective - hinge['x']) - np.arctan2(
hinge['y'] - y_TE_baseline,
x_TE_baseline - hinge['x'])
# Convet to degrees
deflection = deflection * 180. / np.pi
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge,
deflection)
flapped_airfoil = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5)
xf.create_input(airfoil, 'Type 3', airfoil=flapped_airfoil)
xf.call(airfoil,
alfas=alpha,
Reynolds=Reynolds,
iteration=100,
GDES=True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
Cd = Data['CD']
Cl = Data['CL']
elif type == 'Same Cl':
current_Cl = 0
current_Cd = 0
previous_Cl = 0
deflection = 2.
history = []
# Rough search
step = 2.
while current_Cl < Cl_objective and deflection < 90.: # Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
print deflection
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap,
hinge, deflection)
flapped_airfoil = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5)
xf.create_input(airfoil, 'Type 3', airfoil=flapped_airfoil)
xf.call(airfoil,
alfas=alpha,
Reynolds=Reynolds,
iteration=100,
GDES=True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
for i in range(1, 6):
# Fine search
step = 0.5**i
current_Cl = previous_Cl
while current_Cl < Cl_objective and deflection < 90.: # Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap,
hinge, deflection)
previous_flapped_airfoil = flapped_airfoil
flapped_airfoil = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5)
xf.create_input(airfoil, 'Type 3', airfoil=flapped_airfoil)
xf.call(airfoil,
alfas=alpha,
Reynolds=Reynolds,
iteration=100,
GDES=True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
print current_Cl, deflection
elif type == 'Same Cd':
current_Cl = 0
current_Cd = 0
previous_Cl = 0
deflection = 2.
history = []
# Rough search
step = 2.
while current_Cd < Cd_objective and deflection < 90.: # Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
print deflection
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap,
hinge, deflection)
flapped_airfoil = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5)
xf.create_input(airfoil, 'Type 3', airfoil=flapped_airfoil)
xf.call(airfoil,
alfas=alpha,
Reynolds=Reynolds,
iteration=100,
GDES=True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
for i in range(1, 6):
# Fine search
step = 0.5**i
current_Cd = previous_Cd
while current_Cd < Cd_objective or deflection < 90.: # Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap,
hinge, deflection)
previous_flapped_airfoil = flapped_airfoil
flapped_airfoil = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5)
xf.create_input(airfoil, 'Type 3', airfoil=flapped_airfoil)
xf.call(airfoil,
alfas=alpha,
Reynolds=Reynolds,
iteration=1000,
GDES=True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
print deflection
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
print current_Cd, deflection
print history
print Cd_objective
deflection = previous_deflection
Cd = previous_Cd
Cl = previous_Cl
flapped_airfoil = previous_flapped_airfoil
elif type == 'Range of deflection':
current_Cl = 0
current_Cd = 0
previous_Cl = 0
deflection = init_deflection
history = {'CD': [], 'CL': [], 'deflection': []}
# Rough search
while deflection < max_deflection: # Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
deflection = deflection + step
print deflection
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap,
hinge, deflection)
flapped_airfoil = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
N=5)
xf.create_input(airfoil, 'Type 3', airfoil=flapped_airfoil)
xf.call(airfoil,
alfas=alpha,
Reynolds=Reynolds,
iteration=300,
GDES=True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
print deflection
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
if deflection <= max_deflection:
history['CD'].append(current_Cd)
history['CL'].append(current_Cl)
history['deflection'].append(deflection)
return history
return deflection, Cd, Cl, flapped_airfoil
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
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge,
deflection)
flapped_airfoil, i_separator = clean(upper_static,
upper_rotated,
lower_static,
lower_rotated,
hinge,
deflection,
return_flap_i=True,
unit_deflection='deg')
#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
#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 find_deflection(x_hinge, upper_cruise, lower_cruise,
type = 'Match trailing edge', alpha=0, Reynolds = 0,
**kwargs):
"""
Function to calculate the flap deflection.
Required inputs:
:param x_hinge
:param upper_cruise
:param lower_cruise
:param type: can be:
- 'Match trailing edge': will find the deflection where the
baseline's trailing edge matches that of the objective, i.e.
match the the trailing edge of a traditional flap with a
morphing conitunous flap.
- 'Same Cl': will find deflection where Cl of flapped airfoil
is equal to the the objective airfoil.
- 'Range of deflection'
kwrgs arguments for 'Match trailing edge':
:param x_TE_objective
:param y_TE_objective
:param x_TE_baseline
:param y_TE_baseline
kwrgs arguments for 'Same Cl':
:param Cl_objective
kwrgs arguments for 'Same Cd':
:param Cd_objective
kwrgs arguments for 'Range of deflection'
:param max_deflection
Optional arguments:
:param alpha
:param Reynolds
"""
import xfoil_module as xf
airfoil = 'flapped_airfoil'
if type == 'Match trailing edge':
x_TE_objective = kwargs['x_TE_objective']
y_TE_objective = kwargs['y_TE_objective']
x_TE_baseline = kwargs['x_TE_baseline']
y_TE_baseline = kwargs['y_TE_baseline']
elif type == 'Same Cl':
Cl_objective = kwargs['Cl_objective']
elif type == 'Same Cd':
Cd_objective = kwargs['Cd_objective']
elif type == 'Range of deflection':
max_deflection = kwargs['max_deflection']
init_deflection = kwargs['init_deflection']
step = kwargs['step']
hinge = find_hinge(x_hinge, upper_cruise, lower_cruise)
upper_static, upper_flap = find_flap(upper_cruise, hinge)
lower_static, lower_flap = find_flap(lower_cruise, hinge)
#==============================================================================
# Find Deflection
#==============================================================================
if type == 'Match trailing edge':
#Calculate deflection angle in radians
deflection = np.arctan2(hinge['y'] - y_TE_objective, x_TE_objective - hinge['x']) - np.arctan2(hinge['y'] - y_TE_baseline, x_TE_baseline - hinge['x'])
# Convet to degrees
deflection = deflection*180./np.pi
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
flapped_airfoil = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5)
xf.create_input(airfoil, 'Type 3', airfoil = flapped_airfoil)
xf.call(airfoil, alfas = alpha, Reynolds = Reynolds, iteration=100, GDES = True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
Cd = Data['CD']
Cl = Data['CL']
elif type == 'Same Cl':
current_Cl = 0
current_Cd = 0
previous_Cl = 0
deflection = 2.
history = []
# Rough search
step = 2.
while current_Cl < Cl_objective and deflection < 90.:# Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
print deflection
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
flapped_airfoil = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5)
xf.create_input(airfoil, 'Type 3', airfoil = flapped_airfoil)
xf.call(airfoil, alfas = alpha, Reynolds = Reynolds, iteration=100, GDES = True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
for i in range(1,6):
# Fine search
step = 0.5**i
current_Cl = previous_Cl
while current_Cl < Cl_objective and deflection < 90.:# Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
previous_flapped_airfoil = flapped_airfoil
flapped_airfoil = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5)
xf.create_input(airfoil, 'Type 3', airfoil = flapped_airfoil)
xf.call(airfoil, alfas = alpha, Reynolds = Reynolds, iteration=100, GDES = True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
print current_Cl, deflection
elif type == 'Same Cd':
current_Cl = 0
current_Cd = 0
previous_Cl = 0
deflection = 2.
history = []
# Rough search
step = 2.
while current_Cd < Cd_objective and deflection < 90.:# Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
print deflection
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
flapped_airfoil = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5)
xf.create_input(airfoil, 'Type 3', airfoil = flapped_airfoil)
xf.call(airfoil, alfas = alpha, Reynolds = Reynolds, iteration=100, GDES = True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
for i in range(1,6):
# Fine search
step = 0.5**i
current_Cd = previous_Cd
while current_Cd < Cd_objective or deflection < 90.:# Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
history.append([previous_deflection, previous_Cl, previous_Cd])
deflection = deflection + step
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
previous_flapped_airfoil = flapped_airfoil
flapped_airfoil = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5)
xf.create_input(airfoil, 'Type 3', airfoil = flapped_airfoil)
xf.call(airfoil, alfas = alpha, Reynolds = Reynolds, iteration=1000, GDES = True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
print deflection
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
print current_Cd, deflection
print history
print Cd_objective
deflection = previous_deflection
Cd = previous_Cd
Cl = previous_Cl
flapped_airfoil = previous_flapped_airfoil
elif type == 'Range of deflection':
current_Cl = 0
current_Cd = 0
previous_Cl = 0
deflection = init_deflection
history = {'CD':[], 'CL':[], 'deflection':[]}
# Rough search
while deflection < max_deflection:# Convet to degrees
previous_Cl = current_Cl
previous_Cd = current_Cd
previous_deflection = deflection
deflection = deflection + step
print deflection
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
flapped_airfoil = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, N = 5)
xf.create_input(airfoil, 'Type 3', airfoil = flapped_airfoil)
xf.call(airfoil, alfas = alpha, Reynolds = Reynolds, iteration=300, GDES = True,
output='Polar')
filename = xf.file_name(airfoil, alpha, output='Polar')
Data = xf.output_reader(filename, output='Polar')
#Rename to make more convenient
print deflection
current_Cd = Data['CD'][0]
current_Cl = Data['CL'][0]
if deflection <= max_deflection:
history['CD'].append(current_Cd)
history['CL'].append(current_Cl)
history['deflection'].append(deflection)
return history
return deflection, Cd, Cl, flapped_airfoil
import numpy as np
import matplotlib.pyplot as plt
import xfoil_module as xf
from CST_module import *
from aero_module import Reynolds
from airfoil_module import CST, create_x
# Au = [0.23993240191629417, 0.34468227138908186, 0.18125405377549103,
# 0.35371349126072665, 0.2440815012119143, 0.25724974995738387]
# Al = [0.18889012559339036, -0.24686758992053115, 0.077569769493868401,
# -0.547827192265256, -0.0047342206759065641, -0.23994805474814629]
Au = [0.172802, 0.167353, 0.130747, 0.172053, 0.112797, 0.168891]
Al = Au
# c_avian = 0.36 #m
# deltaz = 0.0093943568219451313*c_avian
c_avian = 1.
deltaz = 0
airfoil = 'avian'
x = create_x(1., distribution='linear')
y = CST(x, 1., [deltaz / 2., deltaz / 2.], Au=Au, Al=Al)
# Create file for Xfoil to read coordinates
xf.create_input(x, y['u'], y['l'], airfoil, different_x_upper_lower=False)
print 'Reynolds: ', Reynolds(10000, 30, c_avian)
Data = xf.find_coefficients(airfoil,
0.,
Reynolds=Reynolds(10000, 30, c_avian),
iteration=100,
NACA=False)
print Data
upper = {'x': x['upper'], 'y': y['upper']}
lower = {'x': x['lower'], 'y': y['lower']}
x_hinge = 0.75
hinge = find_hinge(x_hinge, upper, lower)
upper_static, upper_flap = find_flap(upper, hinge)
lower_static, lower_flap = find_flap(lower, hinge, extra_points = 'lower')
deflection = -90.
upper_rotated, lower_rotated = rotate(upper_flap, lower_flap, hinge, deflection)
flapped_airfoil, i_separator = clean(upper_static, upper_rotated, lower_static,
lower_rotated, hinge, deflection, return_flap_i = True,
unit_deflection = 'deg')
#~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~
#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_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