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 __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)
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,
'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
]
