text: """
  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 unittest
  import numpy as np
  from os import path
  import math
  
  from wisdem.ccblade import CCAirfoil, CCBlade
  
  
  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
  
          P, T, Q, M = self.rotor.evaluate(Uinf, Omega, pitch)
  
          # 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__':
      unittest.TextTestRunner().run(suite())
  
  