def read_xls(self, sheetName, dbPath=""):
r"""
Parameters
----------
sheetName : string
name of xls sheet with airfoil data
dbPath : path
file path of xls format airfoil database. If dbPath='' then default database will be
used.
Default db path is 'database/airfoil.xls'.
Default paths can be edited in paths.py
Data read are: coordinates, optional: aerodynamic data
"""
if dbPath == "":
dbPath = self.dbPath
dbPath = paths.fixPaths(dbPath) # TODO: update using io.path
db = dbTools.read(dbPath, sheetName)
self.name = sheetName
xCoord = db.readRow(0, 1)
yCoord = db.readRow(1, 1)
self.coord = transpose([xCoord, yCoord])
self.separate_coordinates()
i = db.findHeader("GEOMETRY")
if i == -1:
self.analyze_geometry()
else:
self.thickness = float(db.readRow(i + 1, 1))
self.camber = db.readRow(i + 2, 1)
i = db.findHeader("ANALYSIS")
if i == -1:
self.build_aero_table()
else:
self.polar.source = db.readRow(i + 1, 1)
i = db.findHeader("LIFT COEFFICIENT")
nAlpha = db.findHeader("DRAG COEFFICIENT") - i - 2
self.polar.Mach = array(db.readRow(i + 1, 1))
self.polar.alpha = array(db.readCol(i + 2, 0, nAlpha))
self.polar.cl = db.readRange(i + 2, 1, nAlpha)
i = db.findHeader("DRAG COEFFICIENT")
self.polar.cd = db.readRange(i + 2, 1, nAlpha)
i = db.findHeader("MOMENT COEFFICIENT")
self.polar.cm = db.readRange(i + 2, 1, nAlpha)
self.polar.cl = transpose(self.polar.cl)
self.polar.cd = transpose(self.polar.cd)
self.polar.cm = transpose(self.polar.cm)
self.polar.create_splines(mach=True)
self.polar.calc_clmax()
self.create_splines()
def __init__(self,inputFilePath,flightConditions):
self.results=list()
for i in range(len(flightConditions)):
self.results.append(_results())
self.inputFilePath=paths.fixPaths(inputFilePath)
self.flightConditions=flightConditions
pth=paths.MyPaths()
cmd=pth.avl+' '+inputFilePath
args=shlex.split(cmd,False,os.name=='posix')
self._ps=sp.Popen(args,stdin=sp.PIPE,stderr=sp.PIPE,stdout=sp.PIPE)
self._ps.stderr.close()
self._runFlightConditions(self.flightConditions)
self.rawOutput=str(self._ps.stdout.read()).replace('\r','')
self._processOutput()
self._setStabResults()
def _read_db(self,sheetName='Sheet1',dbPath=''):
if dbPath=='':
dbPath = self.dbPath
dbPath = paths.fixPaths(dbPath)
dragDb = dbTools.loadDB(dbPath)
sheet = dragDb.selectByName(sheetName)
db = dbTools.readDB(sheet)
nComp = sheet.nrows - 1
self.name = db.readCol(1,0,nComp)
self.desc = db.readCol(1,1,nComp)
self.relCD = db.readCol(1,2,nComp)
mode = db.readCol(1,3,nComp)
for m in mode:
if m=='*':
self.mode.append(True)
else:
self.mode.append(False)
def read_xls(self,propName, dbPath=None, afDbPath=None):
"""
reads in excel propeller database. Two database files are needed:
propeller, airfoil.
Parameters
----------
propName : string
propeller name
dbPath : path
path of the propeller database. Default db will be used if not
specified.
afDbPath : path
path of the airfoil database. Default db will be used if not
specified.
"""
if dbPath==None:
dbPath = self.defaultPath.prop
if afDbPath==None:
afDbPath = self.defaultPath.propAirfoil
dbPath = paths.fixPaths(dbPath)
propDb = dbTools.loadDB(dbPath)
sheet = propDb.selectByName(propName)
db = dbTools.readDB(sheet)
self.name = propName
self.diameter = db.readRow(1,1)
self.radius = self.diameter / 2.0
self.hubDiameter = 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*self.r / self.diameter
self.chord = db.readRow(7,1)
self.beta = db.readRow(8,1)
self.airfoilName = db.readRow(9,1)
self.numStations = len(self.r)
self.betaCurrent = 0.0
self.betaXstation = 0.0
for afName in self.airfoilName:
af = airfoil.Airfoil()
af.read_xls(afName,afDbPath)
self.airfoil.append(af)
self.analyze_geometry()
def write_xls(self, dbPath="", includePolars=True):
r"""
Writes airfoil data (geometry, aerodynamics) to database.
Parameters
----------
dbPath : path
file path of airfoil database in xls format. If dbPath is not
specified then default database will be used
"""
if dbPath == "":
dbPath = self.dbPath
dbPath = paths.fixPaths(dbPath)
afDB = dbTools.loadDB(dbPath, mode="w")
newSheet = afDB.add_sheet(self.name)
sheet = dbTools.writeDB(newSheet)
sheet.writeRow("X", self.coord[:, 0])
sheet.writeRow("Y", self.coord[:, 1])
sheet.writeRow("GEOMETRY")
sheet.writeRow("thickness", self.thickness)
sheet.writeRow("camber", self.camber)
if includePolars:
sheet.writeRow("ANALYSIS")
sheet.writeRow("method", self.polar.source)
sheet.writeRow("LIFT COEFFICIENT")
sheet.writeRow("Mach list", self.polar.Mach)
i = sheet._prevRow + 1
sheet.writeCol(self.polar.alpha)
sheet.writeRange(transpose(self.polar.cl), i, 1)
sheet.writeRow("DRAG COEFFICIENT")
sheet.writeRow("Mach list", self.polar.Mach)
i = sheet._prevRow + 1
sheet.writeCol(self.polar.alpha)
sheet.writeRange(transpose(self.polar.cd), i, 1)
sheet.writeRow("MOMENT COEFFICIENT")
sheet.writeRow("Mach list", self.polar.Mach)
i = sheet._prevRow + 1
sheet.writeCol(self.polar.alpha)
sheet.writeRange(transpose(self.polar.cm), i, 1)
afDB.save_db()
def write_xls(self,dbPath='',afDbPath=''):
if dbPath=='':
dbPath = self.defaultPath.prop
if afDbPath=='':
afDbPath = self.defaultPath.propAirfoil
dbPath = paths.fixPaths(dbPath)
print dbPath, afDbPath
db = dbTools.loadDB(dbPath,mode='w')
newSheet = db.add_sheet(self.name)
sheet = dbTools.writeDB(newSheet)
sheet.writeRow('name',self.name)
sheet.writeRow('diameter',self.diameter)
sheet.writeRow('hub diameter',self.hubDiameter)
sheet.writeRow('num blades',self.numBlades)
sheet.writeRow('beta range deg',self.betaRange)
sheet.writeRow('r',self.r)
sheet.writeRow('x',self.x)
sheet.writeRow('chord',self.chord)
sheet.writeRow('beta',self.beta)
sheet.writeRow('airfoils',self.airfoilName)
db.save_db()
for af in self.airfoil:
af.write_xls(afDbPath)
def write_xls(self,dbPath=None,afDbPath=None):
"""
saves propeller and all airfoil sections into propeller and propAirfoil
xls sheets.
Parameters
----------
dbPath : string
path to propeller sheet file. If path is not specified then
default is used
afDbPath : string
path to propelller airfoil sheet file. If path is not specified then
default is used
"""
if dbPath==None:
dbPath = self.defaultPath.prop
if afDbPath==None:
afDbPath = self.defaultPath.propAirfoil
dbPath = paths.fixPaths(dbPath)
print dbPath, afDbPath
db = dbTools.loadDB(dbPath,mode='w')
newSheet = db.add_sheet(self.name)
sheet = dbTools.writeDB(newSheet)
sheet.writeRow('name',self.name)
sheet.writeRow('diameter',self.diameter)
sheet.writeRow('hub diameter',self.hubDiameter)
sheet.writeRow('num blades',self.numBlades)
sheet.writeRow('beta range deg',self.betaRange)
sheet.writeRow('r',self.r)
sheet.writeRow('x',self.x)
sheet.writeRow('chord',self.chord)
sheet.writeRow('beta',self.beta)
sheet.writeRow('airfoils',self.airfoilName)
db.save_db()
for af in self.airfoil:
af.write_xls(afDbPath)
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()