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test_ccblade.py
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"""
Licensed under the Apache License, Version 2.0 (the "License");
you may not use this file except in compliance with the License.
You may obtain a copy of the License at
http://www.apache.org/licenses/LICENSE-2.0
Unless required by applicable law or agreed to in writing, software
distributed under the License is distributed on an "AS IS" BASIS,
WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
See the License for the specific language governing permissions and
limitations under the License.
"""
import math
import unittest
from os import path
import numpy as np
from ccblade.ccblade import CCBlade, CCAirfoil
class TestNREL5MW(unittest.TestCase):
def setUp(self):
# geometry
Rhub = 1.5
Rtip = 63.0
r = np.array(
[
2.8667,
5.6000,
8.3333,
11.7500,
15.8500,
19.9500,
24.0500,
28.1500,
32.2500,
36.3500,
40.4500,
44.5500,
48.6500,
52.7500,
56.1667,
58.9000,
61.6333,
]
)
chord = np.array(
[
3.542,
3.854,
4.167,
4.557,
4.652,
4.458,
4.249,
4.007,
3.748,
3.502,
3.256,
3.010,
2.764,
2.518,
2.313,
2.086,
1.419,
]
)
theta = np.array(
[
13.308,
13.308,
13.308,
13.308,
11.480,
10.162,
9.011,
7.795,
6.544,
5.361,
4.188,
3.125,
2.319,
1.526,
0.863,
0.370,
0.106,
]
)
B = 3 # number of blades
# atmosphere
rho = 1.225
mu = 1.81206e-5
afinit = CCAirfoil.initFromAerodynFile # just for shorthand
basepath = path.join(path.dirname(path.realpath(__file__)), "5MW_AFFiles")
# load all airfoils
airfoil_types = [0] * 8
airfoil_types[0] = afinit(path.join(basepath, "Cylinder1.dat"))
airfoil_types[1] = afinit(path.join(basepath, "Cylinder2.dat"))
airfoil_types[2] = afinit(path.join(basepath, "DU40_A17.dat"))
airfoil_types[3] = afinit(path.join(basepath, "DU35_A17.dat"))
airfoil_types[4] = afinit(path.join(basepath, "DU30_A17.dat"))
airfoil_types[5] = afinit(path.join(basepath, "DU25_A17.dat"))
airfoil_types[6] = afinit(path.join(basepath, "DU21_A17.dat"))
airfoil_types[7] = afinit(path.join(basepath, "NACA64_A17.dat"))
# place at appropriate radial stations
af_idx = [0, 0, 1, 2, 3, 3, 4, 5, 5, 6, 6, 7, 7, 7, 7, 7, 7]
af = [0] * len(r)
for i in range(len(r)):
af[i] = airfoil_types[af_idx[i]]
tilt = -5.0
precone = 2.5
yaw = 0.0
# create CCBlade object
self.rotor = CCBlade(r, chord, theta, af, Rhub, Rtip, B, rho, mu, precone, tilt, yaw, shearExp=0.2, hubHt=90.0)
def test_thrust_torque(self):
Uinf = np.array([3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25])
Omega = np.array(
[
6.972,
7.183,
7.506,
7.942,
8.469,
9.156,
10.296,
11.431,
11.890,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
12.100,
]
)
pitch = np.array(
[
0.000,
0.000,
0.000,
0.000,
0.000,
0.000,
0.000,
0.000,
0.000,
3.823,
6.602,
8.668,
10.450,
12.055,
13.536,
14.920,
16.226,
17.473,
18.699,
19.941,
21.177,
22.347,
23.469,
]
)
Pref = np.array(
[
42.9,
188.2,
427.9,
781.3,
1257.6,
1876.2,
2668.0,
3653.0,
4833.2,
5296.6,
5296.6,
5296.6,
5296.6,
5296.6,
5296.6,
5296.6,
5296.6,
5296.7,
5296.6,
5296.7,
5296.6,
5296.6,
5296.7,
]
)
Tref = np.array(
[
171.7,
215.9,
268.9,
330.3,
398.6,
478.0,
579.2,
691.5,
790.6,
690.0,
608.4,
557.9,
520.5,
491.2,
467.7,
448.4,
432.3,
418.8,
406.7,
395.3,
385.1,
376.7,
369.3,
]
)
Qref = np.array(
[
58.8,
250.2,
544.3,
939.5,
1418.1,
1956.9,
2474.5,
3051.1,
3881.3,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
4180.1,
]
)
m_rotor = 110.0 # kg
g = 9.81
tilt = 5 * math.pi / 180.0
Tref -= m_rotor * g * math.sin(tilt) # remove weight of rotor that is included in reported results
outputs, derivs = self.rotor.evaluate(Uinf, Omega, pitch)
P, T, Q = [outputs[key] for key in ("P", "T", "Q")]
# import matplotlib.pyplot as plt
# plt.plot(Uinf, P/1e6)
# plt.plot(Uinf, Pref/1e3)
# plt.figure()
# plt.plot(Uinf, T/1e6)
# plt.plot(Uinf, Tref/1e3)
# plt.show()
idx = Uinf < 15
np.testing.assert_allclose(Q[idx] / 1e6, Qref[idx] / 1e3, atol=0.15)
np.testing.assert_allclose(P[idx] / 1e6, Pref[idx] / 1e3, atol=0.2) # within 0.2 of 1MW
np.testing.assert_allclose(T[idx] / 1e6, Tref[idx] / 1e3, atol=0.15)
def suite():
suite = unittest.TestSuite()
suite.addTest(unittest.makeSuite(TestNREL5MW))
return suite
if __name__ == "__main__":
result = unittest.TextTestRunner().run(suite())
if result.wasSuccessful():
exit(0)
else:
exit(1)