def fit_airfoil():
import airfoil
af = airfoil.load('GA37A315mod')
curveUp = interp1d(af.ptsUp[:,0],af.ptsUp[:,1],'cubic')
curveLo = interp1d(af.ptsLo[:,0],af.ptsLo[:,1],'cubic')
args = (curveUp,curveLo,)
def func(x,curveUp,curveLo):
ptsUp,ptsLo = get_bezier_airfoil(x)
err = 0.0
for pt in ptsUp:
err += (curveUp(pt[0])-pt[1])**2.0
for pt in ptsLo:
err += (curveLo(pt[0])-pt[1])**2.0
return err
x0 = np.array([0.03,0.04,0.06,0.04, 0.01,0.01,-0.03])
rslt = minimize(func,x0,method='SLSQP',args=args)
ptsUp,ptsLo = get_bezier_airfoil(rslt.x,30)
plt.figure()
plt.hold(True)
plt.plot(ptsUp[:,0],ptsUp[:,1],'r-')
plt.plot(ptsLo[:,0],ptsLo[:,1],'r-')
plt.plot(af.pts[:,0],af.pts[:,1],'k--')
plt.axis('equal')
plt.show()
def _load_airfoils(self,xlsPath=None):
if xlsPath==None:
xlsPath = path.db.airfoil
self.secThickness = np.zeros(self.nSec)
for i,name in enumerate(self.airfoilNames):
self.airfoils.append(airfoil.load(name))
self.secThickness[i] = self.airfoils[i].thickness
def read_db(self,name,xlsPath=None,airfoilXlsPath=None):
if xlsPath==None:
xlsPath = pth.db.prop
if airfoilXlsPath==None:
airfoilXlsPath = pth.db.propAirfoil
sh = db_tools.ReadDatabase(xlsPath,name)
self.name = name
self.diameter = sh.read_row(1,1)
self.diameterHub = sh.read_row(-1,1)
self.numBlades = sh.read_row(-1,1)
self.betaRange = sh.read_row(-1,1)
self.r = sh.read_row(-1,1)
self.chord = sh.read_row(-1,1)
self.beta = sh.read_row(-1,1)
self.airfoilNames = sh.read_row(-1,1)
self._numSections = len(self.r)
for afname in self.airfoilNames:
self.airfoils.append(airfoil.load(afname, airfoilXlsPath))
self._analyze_geometry()
def read_xls(self,name,dbPath='',afDbPath=''):
if dbPath=='':
dbPath = self.defaultPath.prop
if afDbPath=='':
afDbPath = self.defaultPath.propAirfoil
dbPath = paths.fixPaths(dbPath)
propDb = dbTools.loadDB(dbPath)
sheet = propDb.selectByName(name)
db = dbTools.readDB(sheet)
self.name = name
self.diameter = db.readRow(1,1)
self.hubDiam = db.readRow(2,1)
self.numBlades= db.readRow(3,1)
self.betaRange= db.readRow(4,1)
self.r = db.readRow(5,1)
self.x = 2.0*self.r / self.diameter
self.chord = db.readRow(7,1)
self.beta = db.readRow(8,1)
afname = db.readRow(9,1)
self.airfoil = list()
for afn in afname:
af = airfoil.load(afn)
self.airfoil.append(af)
self._get_prop_data()
def create_with_airfoil_name(self,name,diam,numBlade,hubDiam,chord,beta,airfoilName,x,betaSet):
afList = list()
for afName in airfoilName:
af = airfoil.load(afName)
afList.append(af)
self.create_with_airfoil(self,name,diam,numBlade,hubDiam,chord,beta,afList,x,betaSet)
def run_test_01():
af1 = af.load('GA37A315')
fit = CSTfit()
fit.fit(af1.upPts)
