def __init__(self):
super().__init__()
self.af_left = Airfoil()
self.af_right = Airfoil()
self.it_point_list_right = []
self.it_point_list_left = []
self.af_left.data_changed.connect(self.connect_airfoils)
self.af_right.data_changed.connect(self.connect_airfoils)
def generator():
"""
generates airofil data for defined set of airfoils
consider paths
"""
for name in ['mh114', 'mh115', 'mh117']:
airfoil = Airfoil(
'XFOIL',
r'E:/propeller/mh_airofils/{}/{}xfoil.txt'.format(name, name))
generate(airfoil,
r'E:\propeller\qprop\airfoildata\{}.txt'.format(name))
def foilProps(self):
# -------------------------------------------------------------------------------
# section to define airfoils and local properties
# -------------------------------------------------------------------------------
def foilname(t):
""" return airfoil name for given thickness, in % chord """
# thicknesses = np.array([9.8, 11, 13, 14.7, 16.2])
# names = ['mh117','mh115', 'mh114','mh113','mh112' ]
thicknesses = np.array([.05])
names = ['mh117']
return 'mh117'
a = np.insert(thicknesses, 0, 0)
thresholds = thicknesses - 0.5 * (thicknesses - a[:-1])
for i in range(len(thresholds) - 1):
if t < thresholds[i + 1] and t > thresholds[i]:
return names[i]
return names[i + 1]
self.airfoils = []
self.airfoilsdata = [] # use this to load preevaluated airofil data
# list of airfoil objects for each radial postion
for i in range(self.N_stations):
# print(foilname(self.t[i] / self.chord[i]*100))
self.airfoils.append(
Airfoil('XFOIL',
r'E:/propeller/mh_airofils/{}/{}xfoil.txt'.format(
foilname(self.ts[i] * 100),
foilname(self.ts[i] * 100)),
origin=0))
for name in ['mh112', 'mh113', 'mh114', 'mh115', 'mh117']:
self.airfoilsdata.append(
np.loadtxt(
r'E:\propeller\qprop\airfoildata\{}.txt'.format(name)))
def returnX(name):
i = 0
for nm in ['mh112', 'mh113', 'mh114', 'mh115', 'mh117']:
if nm == name:
return self.airfoilsdata[i]
i += 1
# arrays of airofil properties
self.Cl0 = np.zeros(self.N_stations)
self.Cla = np.zeros(self.N_stations)
self.Cd0 = np.zeros(self.N_stations)
self.ClCd0 = np.zeros(self.N_stations)
self.Cd2u = np.zeros(self.N_stations)
self.Cd2l = np.zeros(self.N_stations)
self.m = self.rs * 2 * self.rpm * np.pi / 60. / 340.
self.re = self.m * 340 * self.chords / 1.42e-5
print('\nr [m]\tchord\tfoil\tmach\tRe')
for i in range(self.N_stations):
print('{:.2f}\t{:.2f}\t{}\t{:.2f}\t{:.1f}'.format(
self.rs[i], self.chords[i], foilname(self.ts[i] * 100),
self.m[i], self.re[i]))
for i in range(self.N_stations):
# first option when dont have airfoil data
# second uses preevaluated airofil polar data
# self.Cl0[i], self.Cla[i], self.Cd0[i], self.ClCd0[i], self.Cd2u[i], self.Cd2l[i] = self.airfoils[i].qpropData(self.m[i], self.re[i])
self.Cl0[i], self.Cla[i], self.Cd0[i], self.ClCd0[i], self.Cd2u[
i], self.Cd2l[i] = readQPolar(
self.re[i],
X=returnX(foilname(self.ts[i] / self.chords[i] * 100)))
self.Clmin = np.ones(self.N_stations) * .2
self.Clmax = np.ones(self.N_stations) * 1
self.Reref = self.chords * self.rs
def genAirfoil(self, t=0):
""" generate airfoil"""
return Airfoil('XFOIL', self.xfoil, t=t)
def get_airfoil(self, obj, numpoints=50, curvature_factor=0.5):
coordinates = self.discretize(obj, numpoints, curvature_factor)
return Airfoil(coordinates)
def genAirfoil(self, t=0):
return Airfoil('XY', x=self.x, y=self.y, t=t)
