def test_blend1_w_airfoil(self):
af1 = Airfoil([self.polar1])
af2 = Airfoil([self.polar2])
af3 = af1.blend(af2, 0.5)
polar3 = af3.polars[0] # kind of bad practice for me to be accessing this
alpha_blend = [-3.04, -2.03, -1.01, 0.01, 1.03, 2.05, 3.07, 4.09,
5.11, 6.13, 7.14, 8.16, 9.17, 10.18, 11.18, 12.19,
13.18, 14.18, 15.18, 16.17, 17.14, 18.06, 19.06, 20.07,
25]
cl_blend = [-0.078, 0.048, 0.158, 0.265, 0.372, 0.479, 0.589, 0.695,
0.801, 0.894, 0.971, 1.041, 1.101, 1.159, 1.162, 1.205,
1.252, 1.225, 1.181, 1.109, 1.045, 0.992, 0.875, 0.877,
1.200]
cd_blend = [0.0134, 0.0117, 0.0125, 0.0147, 0.0150, 0.0154, 0.0162,
0.0172, 0.0178, 0.0190, 0.0210, 0.0237, 0.0273, 0.0373,
0.0598, 0.0497, 0.0490, 0.0737, 0.0822, 0.1131, 0.1620,
0.3101, 0.3101, 0.3101, 0.4000]
# re-interpolate b/c angles of attack are different
cl3 = np.interp(alpha_blend, polar3.alpha, polar3.cl)
cd3 = np.interp(alpha_blend, polar3.alpha, polar3.cd)
# should be within 1e-3
np.testing.assert_allclose(cl3, cl_blend, atol=1e-3)
np.testing.assert_allclose(cd3, cd_blend, atol=1e-3)
def test_stall1_w_airfoil(self):
R = 2.4
r = 0.25*R
chord = 0.18
Omega = 200*pi/30
Uinf = 10.0
tsr = Omega*R/Uinf
af = Airfoil([self.polar])
newaf = af.correction3D(r/R, chord/r, tsr,
alpha_max_corr=30,
alpha_linear_min=-4,
alpha_linear_max=4)
newpolar = newaf.polars[0]
cl_3d = [-0.8466, -0.7523, -0.6420, -0.5342, -0.4302, -0.3284,
-0.2276, -0.1303, -0.0404, 0.0618, 0.2191, 0.3321, 0.4336,
0.5501, 0.6755, 0.7363, 0.8101, 0.8973, 0.9810, 1.0640,
1.1450, 1.2098, 1.2682, 1.3281, 1.3731, 1.3088, 1.3159,
1.3534, 1.4010, 1.4515, 1.9140, 1.8857, 1.6451]
cd_3d = [0.0399, 0.0334, 0.0316, 0.0293, 0.0269, 0.0254, 0.0246,
0.0246, 0.0246, 0.0252, 0.0249, 0.0200, 0.0167, 0.0157,
0.0174, 0.0183, 0.0212, 0.0255, 0.0303, 0.0367, 0.0465,
0.0615, 0.0800, 0.1047, 0.1301, 0.1695, 0.2047, 0.2384,
0.2728, 0.3081, 0.8097, 1.2625, 1.6280]
# test equality
np.testing.assert_allclose(newpolar.cl, cl_3d, atol=1e-3)
np.testing.assert_allclose(newpolar.cd, cd_3d, atol=1e-3)
def test_blend1_w_airfoil(self):
af1 = Airfoil([self.polar1])
af2 = Airfoil([self.polar2])
af3 = af1.blend(af2, 0.5)
polar3 = af3.polars[
0] # kind of bad practice for me to be accessing this
alpha_blend = [
-3.04, -2.03, -1.01, 0.01, 1.03, 2.05, 3.07, 4.09, 5.11, 6.13,
7.14, 8.16, 9.17, 10.18, 11.18, 12.19, 13.18, 14.18, 15.18, 16.17,
17.14, 18.06, 19.06, 20.07, 25
]
cl_blend = [
-0.078, 0.048, 0.158, 0.265, 0.372, 0.479, 0.589, 0.695, 0.801,
0.894, 0.971, 1.041, 1.101, 1.159, 1.162, 1.205, 1.252, 1.225,
1.181, 1.109, 1.045, 0.992, 0.875, 0.877, 1.200
]
cd_blend = [
0.0134, 0.0117, 0.0125, 0.0147, 0.0150, 0.0154, 0.0162, 0.0172,
0.0178, 0.0190, 0.0210, 0.0237, 0.0273, 0.0373, 0.0598, 0.0497,
0.0490, 0.0737, 0.0822, 0.1131, 0.1620, 0.3101, 0.3101, 0.3101,
0.4000
]
# re-interpolate b/c angles of attack are different
cl3 = np.interp(alpha_blend, polar3.alpha, polar3.cl)
cd3 = np.interp(alpha_blend, polar3.alpha, polar3.cd)
# should be within 1e-3
np.testing.assert_allclose(cl3, cl_blend, atol=1e-3)
np.testing.assert_allclose(cd3, cd_blend, atol=1e-3)
def test_stall1_w_airfoil(self):
R = 2.4
r = 0.25 * R
chord = 0.18
Omega = 200 * pi / 30
Uinf = 10.0
tsr = Omega * R / Uinf
af = Airfoil([self.polar])
newaf = af.correction3D(r / R,
chord / r,
tsr,
alpha_max_corr=30,
alpha_linear_min=-4,
alpha_linear_max=4)
_, _, cl_grid, cd_grid, cm_grid = newaf.createDataGrid()
newpolar = newaf.polars[0]
cl_3d = [
-0.8466, -0.7523, -0.6420, -0.5342, -0.4302, -0.3284, -0.2276,
-0.1303, -0.0404, 0.0618, 0.2191, 0.3321, 0.4336, 0.5501, 0.6755,
0.7363, 0.8101, 0.8973, 0.9810, 1.0640, 1.1450, 1.2098, 1.2682,
1.3281, 1.3731, 1.3088, 1.3159, 1.3534, 1.4010, 1.4515, 1.9140,
1.8857, 1.6451
]
cd_3d = [
0.0399, 0.0334, 0.0316, 0.0293, 0.0269, 0.0254, 0.0246, 0.0246,
0.0246, 0.0252, 0.0249, 0.0200, 0.0167, 0.0157, 0.0174, 0.0183,
0.0212, 0.0255, 0.0303, 0.0367, 0.0465, 0.0615, 0.0800, 0.1047,
0.1301, 0.1695, 0.2047, 0.2384, 0.2728, 0.3081, 0.8097, 1.2625,
1.6280
]
cm_test = [[-0.0037], [-0.0044], [-0.0051], [0.0018], [-0.0216],
[-0.0282], [-0.0346], [-0.0405], [-0.0455], [-0.0507],
[-0.0404], [-0.0321], [-0.0281], [-0.0284], [-0.0322],
[-0.0361], [-0.0363], [-0.0393], [-0.0398], [-0.0983],
[-0.1242], [-0.1155], [-0.1068], [-0.0981], [-0.0894],
[-0.0807], [-0.072], [-0.0633], [-0.054], [-0.045],
[-0.036], [-0.22], [-0.13]]
# test equality
np.testing.assert_allclose(newpolar.cl, cl_3d, atol=1e-3)
np.testing.assert_allclose(newpolar.cd, cd_3d, atol=1e-3)
np.testing.assert_allclose(cm_grid, cm_test, atol=1e-3)
def test_extrap1_w_airfoil(self):
cdmax = 1.29
af = Airfoil([self.polar2])
newaf = af.extrapolate(cdmax=cdmax)
newpolar = newaf.polars[0]
alpha_extrap = [
-180, -170, -160, -150, -140, -130, -120, -110, -100, -90, -80,
-70, -60, -50, -40, -30, -20, -10.1, -8.2, -6.1, -4.1, -2.1, 0.1,
2, 4.1, 6.2, 8.1, 10.2, 11.3, 12.1, 13.2, 14.2, 15.3, 16.3, 17.1,
18.1, 19.1, 20.1, 30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130,
140, 150, 160, 170, 180
]
cl_extrap = [
0.0000, 0.2299, 0.4597, 0.4907, 0.5053, 0.4805, 0.4102, 0.2985,
0.1565, 0.0000, -0.1565, -0.2985, -0.4102, -0.4805, -0.5053,
-0.4907, -0.4637, -0.6300, -0.5600, -0.6400, -0.4200, -0.2100,
0.0500, 0.3000, 0.5400, 0.7900, 0.9000, 0.9300, 0.9200, 0.9500,
0.9900, 1.0100, 1.0200, 1.0000, 0.9400, 0.8500, 0.7000, 0.6600,
0.7010, 0.7219, 0.6864, 0.5860, 0.4264, 0.2235, 0.0000, -0.1565,
-0.2985, -0.4102, -0.4805, -0.5053, -0.4907, -0.4597, -0.2299,
0.0000
]
cd_extrap = [
0.1770, 0.2132, 0.3173, 0.4758, 0.6686, 0.8708, 1.0560, 1.1996,
1.2818, 1.2900, 1.2818, 1.1996, 1.0560, 0.8708, 0.6686, 0.4758,
0.3158, 0.0390, 0.0233, 0.0131, 0.0134, 0.0119, 0.0122, 0.0116,
0.0144, 0.0146, 0.0162, 0.0274, 0.0303, 0.0369, 0.0509, 0.0648,
0.0776, 0.0917, 0.0994, 0.2306, 0.3142, 0.3186, 0.4758, 0.6686,
0.8708, 1.0560, 1.1996, 1.2818, 1.2900, 1.2818, 1.1996, 1.0560,
0.8708, 0.6686, 0.4758, 0.3173, 0.2132, 0.1770
]
cm_extrap = np.linspace(0, 0, len(cd_extrap))
# re-interpolate b/c angles of attack are different
cl = np.interp(alpha_extrap, newpolar.alpha, newpolar.cl)
cd = np.interp(alpha_extrap, newpolar.alpha, newpolar.cd)
cm = np.interp(alpha_extrap, newpolar.alpha, newpolar.cm)
# test equality
np.testing.assert_allclose(cl, cl_extrap, atol=1.5e-4)
np.testing.assert_allclose(cd, cd_extrap, atol=1.5e-4)
np.testing.assert_allclose(cm, cm_extrap, atol=5e-3)
def test_extrap1_w_airfoil(self):
cdmax = 1.29
af = Airfoil([self.polar])
newaf = af.extrapolate(cdmax=cdmax)
newpolar = newaf.polars[0]
alpha_extrap = [-180, -170, -160, -150, -140, -130, -120, -110, -100,
-90, -80, -70, -60, -50, -40, -30, -20, -10.1, -8.2,
-6.1, -4.1, -2.1, 0.1, 2, 4.1, 6.2, 8.1, 10.2, 11.3,
12.1, 13.2, 14.2, 15.3, 16.3, 17.1, 18.1, 19.1, 20.1,
30, 40, 50, 60, 70, 80, 90, 100, 110, 120, 130, 140,
150, 160, 170, 180]
cl_extrap = [0.0000, 0.2299, 0.4597, 0.4907, 0.5053, 0.4805, 0.4102,
0.2985, 0.1565, 0.0000, -0.1565, -0.2985, -0.4102,
-0.4805, -0.5053, -0.4907, -0.4637, -0.6300, -0.5600,
-0.6400, -0.4200, -0.2100, 0.0500, 0.3000, 0.5400,
0.7900, 0.9000, 0.9300, 0.9200, 0.9500, 0.9900, 1.0100,
1.0200, 1.0000, 0.9400, 0.8500, 0.7000, 0.6600, 0.7010,
0.7219, 0.6864, 0.5860, 0.4264, 0.2235, 0.0000, -0.1565,
-0.2985, -0.4102, -0.4805, -0.5053, -0.4907, -0.4597,
-0.2299, 0.0000]
cd_extrap = [0.1770, 0.2132, 0.3173, 0.4758, 0.6686, 0.8708, 1.0560,
1.1996, 1.2818, 1.2900, 1.2818, 1.1996, 1.0560, 0.8708,
0.6686, 0.4758, 0.3158, 0.0390, 0.0233, 0.0131, 0.0134,
0.0119, 0.0122, 0.0116, 0.0144, 0.0146, 0.0162, 0.0274,
0.0303, 0.0369, 0.0509, 0.0648, 0.0776, 0.0917, 0.0994,
0.2306, 0.3142, 0.3186, 0.4758, 0.6686, 0.8708, 1.0560,
1.1996, 1.2818, 1.2900, 1.2818, 1.1996, 1.0560, 0.8708,
0.6686, 0.4758, 0.3173, 0.2132, 0.1770]
# re-interpolate b/c angles of attack are different
cl = np.interp(alpha_extrap, newpolar.alpha, newpolar.cl)
cd = np.interp(alpha_extrap, newpolar.alpha, newpolar.cd)
# test equality
np.testing.assert_allclose(cl, cl_extrap, atol=1.5e-4)
np.testing.assert_allclose(cd, cd_extrap, atol=1.5e-4)
def initFromAerodynFile(cls, aerodynFile):
"""convenience method for initializing with AeroDyn formatted files
Parameters
----------
aerodynFile : str
location of AeroDyn style airfoiil file
Returns
-------
af : CCAirfoil
a constructed CCAirfoil object
"""
af = Airfoil.initFromAerodynFile(aerodynFile)
alpha, Re, cl, cd, cm = af.createDataGrid()
return cls(alpha, Re, cl, cd)
def test_stall1_w_airfoil(self):
R = 2.4
r = 0.25 * R
chord = 0.18
Omega = 200 * pi / 30
Uinf = 10.0
tsr = Omega * R / Uinf
af = Airfoil([self.polar])
newaf = af.correction3D(r / R,
chord / r,
tsr,
alpha_max_corr=30,
alpha_linear_min=-4,
alpha_linear_max=4)
newpolar = newaf.polars[0]
cl_3d = [
-0.8466, -0.7523, -0.6420, -0.5342, -0.4302, -0.3284, -0.2276,
-0.1303, -0.0404, 0.0618, 0.2191, 0.3321, 0.4336, 0.5501, 0.6755,
0.7363, 0.8101, 0.8973, 0.9810, 1.0640, 1.1450, 1.2098, 1.2682,
1.3281, 1.3731, 1.3088, 1.3159, 1.3534, 1.4010, 1.4515, 1.9140,
1.8857, 1.6451
]
cd_3d = [
0.0399, 0.0334, 0.0316, 0.0293, 0.0269, 0.0254, 0.0246, 0.0246,
0.0246, 0.0252, 0.0249, 0.0200, 0.0167, 0.0157, 0.0174, 0.0183,
0.0212, 0.0255, 0.0303, 0.0367, 0.0465, 0.0615, 0.0800, 0.1047,
0.1301, 0.1695, 0.2047, 0.2384, 0.2728, 0.3081, 0.8097, 1.2625,
1.6280
]
# test equality
np.testing.assert_allclose(newpolar.cl, cl_3d, atol=1e-3)
np.testing.assert_allclose(newpolar.cd, cd_3d, atol=1e-3)
def __init__(self, path):
fp = open(path)
lines = fp.readlines()
self.NumFoil = int(splitLine(lines[17])[0])
self.foils = []
for i in range(self.NumFoil):
tt = splitLine(lines[18+i])[0][1:-1]
path_af = os.path.join(os.path.dirname(path), tt)
af = Airfoil.initFromAerodynFile(path_af)
self.foils.append(af)
nodeNum = int(splitLine(lines[22])[0])
self.cols = splitLine(lines[23])
_data = []
for i in range(nodeNum):
values = self.splitLine(lines[24+i])
_data.append(values)
self.nodeData = pd.DataFrame(_data, columns=self.cols)
def initFromAerodynFile(cls, aerodynFile):
"""convenience method for initializing with AeroDyn formatted files
Parameters
----------
aerodynFile : str
location of AeroDyn style airfoiil file
Returns
-------
af : CCAirfoil
a constructed CCAirfoil object
"""
af = Airfoil.initFromAerodynFile(aerodynFile)
alpha, Re, cl, cd, cm = af.createDataGrid()
return cls(alpha, Re, cl, cd)
def generate_af(self):
af_type = self.airfoil_parameterization_type
af_parameters = self.airfoil_parameters
if af_type == 'CST':
n = len(self.airfoil_parameters[0])
af = [0]*n
else:
n = len(self.airfoil_parameters)
af = [0]*n
r_over_R = 0.5
chord_over_r = 0.15
tsr = 7.55
cd_max = 1.5
for i in range(n):
x = []
y = []
if af_type == 'Coordinates':
try:
f = open(af_parameters[i],'r')
except:
print 'There was an error opening the airfoil file %s'%(af_parameters[i])
sys.exit(1)
for line in f:
try:
x.append(float(string.split(line)[0]))
y.append(float(string.split(line)[1]))
except:
pass
elif af_type == 'NACA':
if len(str(int(af_parameters[i]))) == 4:
pts = naca4(str(int(af_parameters[i])), 60)
elif len(str(int(af_parameters[i] == 5))):
pts = naca5(str(int(af_parameters[i])), 60)
else:
'Please input only NACA 4 or 5 series'
for j in range(len(pts)):
x.append(pts[j][0])
y.append(pts[j][1])
elif af_type == 'CST':
n = len(af_parameters)/2
wu = np.zeros(n)
wl = np.zeros(n)
for j in range(n):
wu[j] = af_parameters[j][i]
wl[j] = af_parameters[j + n][i]
# wu, wl = np.split(af_parameters[i], 2)
w1 = np.average(wl)
w2 = np.average(wu)
if w1 < w2:
pass
else:
higher = wl
lower = wu
wl = lower
wu = higher
N = 120
dz = 0.
# Populate x coordinates
x = np.ones((N, 1))
zeta = np.zeros((N, 1))
for z in range(0, N):
zeta[z] = 2 * pi / N * z
if z == N - 1:
zeta[z] = 2 * pi
x[z] = 0.5*(cos(zeta[z])+1)
# N1 and N2 parameters (N1 = 0.5 and N2 = 1 for airfoil shape)
N1 = 0.5
N2 = 1
try:
zerind = np.where(x == 0) # Used to separate upper and lower surfaces
zerind = zerind[0][0]
except:
zerind = N/2
xl = np.zeros(zerind)
xu = np.zeros(N-zerind)
for z in range(len(xl)):
xl[z] = np.real(x[z]) # Lower surface x-coordinates
for z in range(len(xu)):
xu[z] = np.real(x[z + zerind]) # Upper surface x-coordinates
yl = self.__ClassShape(wl, xl, N1, N2, -dz) # Call ClassShape function to determine lower surface y-coordinates
yu = self.__ClassShape(wu, xu, N1, N2, dz) # Call ClassShape function to determine upper surface y-coordinates
y = np.concatenate([yl, yu]) # Combine upper and lower y coordinates
y = y[::-1]
# coord_split = [xl, yl, xu, yu] # Combine x and y into single output
# coord = [x, y]
x1 = np.zeros(len(x))
for k in range(len(x)):
x1[k] = x[k][0]
x = x1
else:
print 'Error. Airfoil parameterization type not specified. Please choose Coordinates, NACA, or CST.'
if i < 3:
Re1 = [1e6]
af[0] = CCAirfoil([-180, 0, 180], Re1, [0, 0, 0], [0.5, 0.5, 0.5])
af[1] = CCAirfoil([-180, 0, 180], Re1, [0, 0, 0], [0.5, 0.5, 0.5])
af[2] = CCAirfoil([-180, 0, 180], Re1, [0, 0, 0], [0.35, 0.35, 0.35])
else:
coordinate_points = [x, y]
Re = 1e6
alphas = np.linspace(-20, 20, 80)
airfoil = pyXLIGHT.xfoilAnalysis(coordinate_points)
airfoil.re = Re
airfoil.mach = 0.03
airfoil.iter = 1000
cl = np.zeros(len(alphas))
cd = np.zeros(len(alphas))
cm = np.zeros(len(alphas))
for j in range(len(alphas)):
angle = alphas[j]
cl[j], cd[j], cm[j], lexitflag = airfoil.solveAlpha(angle)
# print cl[j], cd[j], angle
p1 = Polar(Re, alphas, cl, cd, cm)
af_p = Airfoil([p1])
af3D = af_p.correction3D(r_over_R, chord_over_r, tsr)
af_extrap1 = af3D.extrapolate(cd_max)
alpha_ext, Re_ext, cl_ext, cd_ext, cm_ext = af_extrap1.createDataGrid()
af[i] = CCAirfoil(alpha_ext, Re_ext, cl_ext, cd_ext)
return af
import os
basepath = os.path.join(os.path.expanduser("~"), "Dropbox", "NREL", "5MW_files", "5MW_AFFiles")
os.chdir(basepath)
# just to temporarily change PYTHONPATH without installing
import sys
sys.path.append(os.path.expanduser("~") + "/Dropbox/NREL/SysEng/TWISTER/src/twister/rotoraero")
# 1 ---------
from airfoilprep import Polar, Airfoil
import numpy as np
airfoil = Airfoil.initFromAerodynFile("DU21_A17.dat")
# 1 ---------
# 2 ---------
# first polar
Re = 7e6
alpha = [
-14.50,
-12.01,
-11.00,
-9.98,
-8.12,
-7.62,
-7.11,
def test_stall1_w_airfoil(self):
R = 2.4
r = 0.25 * R
chord = 0.18
Omega = 200 * pi / 30
Uinf = 10.0
tsr = Omega * R / Uinf
af = Airfoil([self.polar])
newaf = af.correction3D(r / R, chord / r, tsr, alpha_max_corr=30, alpha_linear_min=-4, alpha_linear_max=4)
_, _, cl_grid, cd_grid, cm_grid = newaf.createDataGrid()
newpolar = newaf.polars[0]
cl_3d = [
-0.8466,
-0.7523,
-0.6420,
-0.5342,
-0.4302,
-0.3284,
-0.2276,
-0.1303,
-0.0404,
0.0618,
0.2191,
0.3321,
0.4336,
0.5501,
0.6755,
0.7363,
0.8101,
0.8973,
0.9810,
1.0640,
1.1450,
1.2098,
1.2682,
1.3281,
1.3731,
1.3088,
1.3159,
1.3534,
1.4010,
1.4515,
1.9140,
1.8857,
1.6451,
]
cd_3d = [
0.0399,
0.0334,
0.0316,
0.0293,
0.0269,
0.0254,
0.0246,
0.0246,
0.0246,
0.0252,
0.0249,
0.0200,
0.0167,
0.0157,
0.0174,
0.0183,
0.0212,
0.0255,
0.0303,
0.0367,
0.0465,
0.0615,
0.0800,
0.1047,
0.1301,
0.1695,
0.2047,
0.2384,
0.2728,
0.3081,
0.8097,
1.2625,
1.6280,
]
cm_test = [
[-0.0037],
[-0.0044],
[-0.0051],
[0.0018],
[-0.0216],
[-0.0282],
[-0.0346],
[-0.0405],
[-0.0455],
[-0.0507],
[-0.0404],
[-0.0321],
[-0.0281],
[-0.0284],
[-0.0322],
[-0.0361],
[-0.0363],
[-0.0393],
[-0.0398],
[-0.0983],
[-0.1242],
[-0.1155],
[-0.1068],
[-0.0981],
[-0.0894],
[-0.0807],
[-0.072],
[-0.0633],
[-0.054],
[-0.045],
[-0.036],
[-0.22],
[-0.13],
]
# test equality
np.testing.assert_allclose(newpolar.cl, cl_3d, atol=1e-3)
np.testing.assert_allclose(newpolar.cd, cd_3d, atol=1e-3)
np.testing.assert_allclose(cm_grid, cm_test, atol=1e-3)
'5MW_files', '5MW_AFFiles')
os.chdir(basepath)
# just to temporarily change PYTHONPATH without installing
import sys
sys.path.append(
os.path.expanduser('~') +
'/Dropbox/NREL/SysEng/TWISTER/src/twister/rotoraero')
# 1 ---------
from airfoilprep import Polar, Airfoil
import numpy as np
airfoil = Airfoil.initFromAerodynFile('DU21_A17.dat')
# 1 ---------
# 2 ---------
# first polar
Re = 7e6
alpha = [
-14.50, -12.01, -11.00, -9.98, -8.12, -7.62, -7.11, -6.60, -6.50, -6.00,
-5.50, -5.00, -4.50, -4.00, -3.50, -3.00, -2.50, -2.00, -1.50, -1.00,
-0.50, 0.00, 0.50, 1.00, 1.50, 2.00, 2.50, 3.00, 3.50, 4.00, 4.50, 5.00,
5.50, 6.00, 6.50, 7.00, 7.50, 8.00, 8.50, 9.00, 9.50, 10.00, 10.50, 11.00,
11.50, 12.00, 12.50, 13.00, 13.50, 14.00, 14.50, 15.00, 15.50, 16.00,
16.50, 17.00, 17.50, 18.00, 18.50, 19.00, 19.50, 20.00, 20.50
]
def solve_nonlinear(self, params, unknowns, resids):
# determine aspect ratio = (rotor radius / chord_75% radius)\
# if provided, cdmax is computed from AR'
bl = params['blade_length']
dr = params['rotor_diameter']
hr = 0.5 * dr - bl
rotor_radius = 0.5 * dr
chord = params['chord_st'] * bl
s = params['s_st']
r = (s * bl + hr) / rotor_radius
chord_75 = np.interp(0.75, r, chord)
AR = rotor_radius / chord_75
# write aerodyn files
af_name_base = 'cs_'
af_name_suffix = '_aerodyn'
tcs = params['cs_polars_tc']
n_cs_alpha = params['n_cs_alpha']
pol = params['cs_polars']
nmet = 0
# TODO: blend polars determined with different methods
for i, tc in enumerate(self.blend_var):
af_name = af_name_base + \
'%03d_%04d' % (i, tc * 1000) + af_name_suffix
re_polars = []
for nre, re in enumerate(self.res):
# create polar object
p = Polar(re,
pol[:n_cs_alpha[i, nre, nmet], 0, i, nre, nmet],
pol[:n_cs_alpha[i, nre, nmet], 1, i, nre, nmet],
pol[:n_cs_alpha[i, nre, nmet], 2, i, nre, nmet],
pol[:n_cs_alpha[i, nre, nmet], 3, i, nre, nmet])
# extrapolate polar
if tc < self.tc_max:
p_extrap = p.extrapolate(self.cdmax,
AR,
self.cdmin,
self.nalpha)
else:
p_extrap = p.extrapolate_as_cylinder()
p_extrap.useCM = self.useCM
re_polars.append(p_extrap)
# TODO: output as HAWC2/FAST format
# See if HAWC can take several af tables with different Re
# numbers
'''
unknowns['airfoildata:aoa%02d' % i] = p_extrap.alpha
unknowns['airfoildata:cl%02d' % i] = p_extrap.cl
unknowns['airfoildata:cd%02d' % i] = p_extrap.cd
unknowns['airfoildata:cm%02d' % i] = p_extrap.cm
'''
# create airfoil object
af = Airfoil(re_polars)
af.interpToCommonAlpha()
af.writeToAerodynFile(af_name + '.dat')
if self.plot_polars:
figs = af.plot(single_figure=True)
titles = ['cl', 'cd', 'cm']
for (fig, title) in zip(figs, titles):
fig.savefig(af_name + '_' + title + '.png', dpi=400)
fig.savefig(af_name + '_' + title + '.pdf')
self._get_unknowns(unknowns)