def _read_xls(self,name=None,dbName=None):
if dbName==None:
dbName = self.pth.engineExp
if name==None:
name = 'ROTAX_912'
engDb = dbTools.loadDB(dbName)
engSh = engDb.selectByName(name)
db = dbTools.readDB(engSh)
idx = db.findHeader('SETTING')
self.rpmLb = np.zeros(len(idx))
self.rpmUb = np.zeros(len(idx))
psetList = np.zeros(len(idx))
for i,j in enumerate(idx):
rpm = db.readRow(j+1,1,True)
psetList[i] = db.readRow(j,1,False)
pset = np.ones(len(rpm))*psetList[i]
self.rpmLb[i] = rpm[0]
self.rpmUb[i] = rpm[-1]
if i==0:
self.powerSetting = pset
self.rpm = rpm
self.power = db.readRow(j+2,1,True)
self.fuelFlow = db.readRow(j+3,1,True)
else:
self.powerSetting = np.hstack([self.powerSetting,pset])
self.rpm = np.hstack([self.rpm,rpm])
self.power = np.hstack([self.power,db.readRow(j+2,1,True)])
self.fuelFlow = np.hstack([self.fuelFlow,db.readRow(j+3,1,True)])
self.rps = self.rpm / 60.0
self.power = self.power * 745.699872 # HP to Watt
self.powerSurf = Rbf(self.powerSetting,self.rpm,self.power)
self.fuelFlowSurf = Rbf(self.powerSetting,self.rpm,self.fuelFlow)
self.rpmLbCurve = interp1d(psetList,self.rpmLb,'cubic')
self.rpmUbCurve = interp1d(psetList,self.rpmUb,'cubic')
self.powerSettingList = psetList
def load(name):
"""
function to load aircraft from xls database.
Parameters
----------
name : string
name of the aircraft configuration (sheet name in db)
Examples
--------
load aircraft configuration from db and store it into *ac* variable
>>> import aircraft
>>> ac = aircraft.load('sampleInput1')
>>> ac.display()
>>> print ac.get_mass_empty() # print empty mass
>>> print ac.get_mass_total() # print total mass
>>> print ac.get_drag() # print total drag
"""
pth=paths.Database()
acDB =dbTools.loadDB(pth.aircraft)
return aircraft(acDB.selectByName(name))
def read_from_db(self,name,dbFile=None):
if dbFile==None:
dbFile = 'LargeTypeASM.xls'
wb = dbTools.loadDB(dbFile,'r')
sh = dbTools.readDB(wb.selectByName(name))
i = sh.findHeader('SECTION: BODY')
self.body.xprofile = sh.readRow(i+1,1,True)
self.body.yprofile = sh.readRow(i+2,1,True)
self.body.set_length(sh.readRow(i+3,1))
self.body.set_diameter(sh.readRow(i+4,1))
i = sh.findHeader('SECTION: WING')
self.wing.chords = sh.readRow(i+1,1,True)
self.wing.incidenceAngle = sh.readRow(i+2,1,True)
self.wing.sectionSpan = sh.readRow(i+3,1)
self.wing.leSweep = sh.readRow(i+4,1)
self.wing.dihedral = sh.readRow(i+5,1)
self.wing._set_airfoil(sh.readRow(i+6,1))
self.wing.location = sh.readRow(i+7,1)
i = sh.findHeader('SECTION: TAIL')
self.tail.chords = sh.readRow(i+1,1,True)
self.tail.incidenceAngle = sh.readRow(i+2,1,True)
self.tail.sectionSpan = sh.readRow(i+3,1)
self.tail.leSweep = sh.readRow(i+4,1)
self.tail.dihedral = sh.readRow(i+5,1)
self.tail._set_airfoil(sh.readRow(i+6,1))
self.tail.location = sh.readRow(i+7,1)
self.tail.xangle = sh.readRow(i+8,1)
self.tail.centerOffset = sh.readRow(i+9,1)
self.tail.elevatorChordRatio = sh.readRow(i+10,1)
def write_to_db(self,name,dbFile=None):
if dbFile==None:
dbFile = 'LargeTypeASM.xls'
db = dbTools.loadDB(dbFile,mode='w')
sh = dbTools.writeDB(db.add_sheet(name))
sh.writeRow('SECTION: BODY')
sh.writeRow('x profile',self.body.xprofile)
sh.writeRow('y profile',self.body.yprofile)
sh.writeRow('length',self.body.length)
sh.writeRow('diameter',self.body.diameter)
sh.writeRow('SECTION: WING')
sh.writeRow('chords',self.wing.chords)
sh.writeRow('incidence',self.wing.incidenceAngle)
sh.writeRow('span',self.wing.sectionSpan)
sh.writeRow('leading edge sweep',self.wing.leSweep)
sh.writeRow('dihedral',self.wing.dihedral)
sh.writeRow('airfoil',self.wing.airfoilPath)
sh.writeRow('location X,Z',self.wing.location)
sh.writeRow('SECTION: TAIL')
sh.writeRow('chords',self.tail.chords)
sh.writeRow('incidence',self.tail.incidenceAngle)
sh.writeRow('span',self.tail.sectionSpan)
sh.writeRow('leading edge sweep',self.tail.leSweep)
sh.writeRow('dihedral',self.tail.dihedral)
sh.writeRow('airfoil',self.tail.airfoilPath)
sh.writeRow('location X,Z',self.tail.location)
sh.writeRow('tail X-angle',self.tail.xangle)
sh.writeRow('tail center offset', self.tail.centerOffset)
sh.writeRow('elevator chord ratio',self.tail.elevatorChordRatio)
db.save_db()
def __init__(self,nameList,CG_X,CG_Y,CG_Z):
"""
Parameters
----------
nameList : list, string
list of engine names
CG_X : float, meters
x coordinate of engine CG
CG_Y : float, meters
y coordinate of engine CG
CG_Z : float, meters
z coordinate of engine CG
"""
pth=paths.Database()
self.CG_X =CG_X
self.CG_Y =CG_Y
self.CG_Z =CG_Z
self.engineList =list()
database =dbTools.loadDB(pth.engine)
if type(nameList)==type(list()):
self.nameList=nameList
else:
self.nameList=list()
self.nameList.append(nameList)
for name in self.nameList:
dataSheet=database.selectByName(name)
self.engineList.append(eng.pistonEngine(dataSheet))
def read_exp_data():
wbName = r'D:\propeller_results.xls'
wb = dbTools.loadDB(wbName)
sh = wb.selectByName('Sheet1')
sh = dbTools.readDB(sh)
J = list()
J.append(sh.readCol(3,0,13))
# J.append(sh.readCol(3,2,17))
# J.append(sh.readCol(3,4,18))
J.append(sh.readCol(3,6,21))
# J.append(sh.readCol(3,8,17))
# J.append(sh.readCol(3,10,16))
J.append(sh.readCol(3,12,17))
effy = list()
effy.append(sh.readCol(3,1,13))
# effy.append(sh.readCol(3,3,17))
# effy.append(sh.readCol(3,5,18))
effy.append(sh.readCol(3,7,21))
# effy.append(sh.readCol(3,9,17))
# effy.append(sh.readCol(3,11,16))
effy.append(sh.readCol(3,13,17))
return J, effy
def runTest():
import paths
db =paths.Database()
engineDB =dbTools.loadDB(db.engine)
engineSheet =engineDB.selectByName("ROTAX_912ULS")
eng =pistonEngine(engineSheet,False)
print eng.get_availablePower(1.05,2000.,100)
print eng.sfc[0]
print eng.get_idle_parameters()
def read_data():
import dbTools
dbname = r'D:\light aircraft\V05\propeller analysis\elprop_results\prop_results.xls'
sheetname = ['15deg_2000rpm','25deg_2000rpm','35deg_2000rpm']
wb = dbTools.loadDB(dbname)
J = list()
effy = list()
for name in sheetname:
sh = dbTools.readDB(wb.selectByName(name))
J.append(sh.readCol(0,3,30))
effy.append(sh.readCol(0,11,30))
return J,effy
def load(name):
"""
function to load aircraft from xls database.
Parameters
----------
name : string
name of the aircraft configuration (sheet name in db)
"""
pth=paths.Database()
acDB =dbTools.loadDB(pth.aircraft)
return aircraft(acDB.selectByName(name))
def write_xls_data(dbPath,name,J,CP,CT,effy,betaRange):
db = dbTools.loadDB(dbPath,mode='w')
newSheet = db.add_sheet(name)
sh = dbTools.writeDB(newSheet)
for i,beta in enumerate(betaRange):
sh.writeRow('beta:',float(beta))
sh.writeRow('J',['effy','CP','CT'])
for j in range(len(J[i])):
nyu = effy[i][j]
cp = CP[i][j]
ct = CT[i][j]
if nyu!=None and cp!=None and ct!=None:
line = [J[i][j], nyu, cp, ct]
sh.writeRow('',line)
sh._prevRow +=1
db.save_db()
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 __init__(self,nameList,propHub_X,propHub_Y,propHub_Z,minBeta,maxBeta):
pth=paths.Database()
self.hub_X =propHub_X
self.hub_Y =propHub_Y
self.hub_Z =propHub_Z
self.betaRange =[minBeta,maxBeta]
self._database =dbTools.loadDB(pth.prop)
if type(nameList)==type(list()):
self.nameList=nameList
else:
self.nameList=list()
self.nameList.append(nameList)
self.propellerList =list()
for i,name in enumerate(self.nameList):
P=prop.propeller()
P.read_xls(name)
betaLo=self.betaRange[0][i]
betaHi=self.betaRange[1][i]
P.betaRange=[betaLo,betaHi]
self.propellerList.append(P)
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 read_exp_data():
dataPath = r'D:\engauge\propeller\digitized_results.xls'
wb = dbTools.loadDB(dataPath)
db = dbTools.readDB(wb.selectByName('NACA5868-9'))
J = list()
CP = list()
CT = list()
J.append(db.readCol(2,0,10))
J.append(db.readCol(2,3,13))
J.append(db.readCol(2,6,13))
J.append(db.readCol(2,9,13))
CP.append(db.readCol(2,1,10))
CP.append(db.readCol(2,4,13))
CP.append(db.readCol(2,7,13))
CP.append(db.readCol(2,10,13))
CT.append(db.readCol(2,2,10))
CT.append(db.readCol(2,5,13))
CT.append(db.readCol(2,8,13))
CT.append(db.readCol(2,11,13))
return J, CP, CT
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()
def runTest1():
pth=paths.Database()
acDB =dbTools.loadDB(pth.aircraft)
#acDB=dbTools.loadDB("//database//aircraft.xls")
workbook = acDB.workbook
worksheets = workbook.sheet_names()
for worksheet_name in worksheets:
worksheet = workbook.sheet_by_name(worksheet_name)
print worksheet
sheetList,sheetNames=acDB.loadData()
print sheetList
print sheetNames
acData=acDB.selectByName("sampleInput1")
print acData
ac=aircraft(acData)
ac=load("sampleInput2")
print ac.wing.airfoilName
print ac.wing.aapex
print ac.wing.incidence
print ac.engine.CG_X
print ac.landingGear.groundContact_X
print ac.VLMsetup.wing_spanwise
print ac.mass[0].name
print ac.mass.nameList()
print 'HT'
print ac.hStab.segmentDihedrals
print ac.hStab.segmentOffsets
print ac.vStab.segmentSpans
ac.mass.removeItem("passenger")
print ac.wing.airfoilName
print ac.fuselage.sideProfile_X
print ac.mass.nameList()
print ac.engine.nameList
print ac.propeller.nameList
print ac.engine.engineList[0].RPM
def __init__(self):
pth=paths.Database()
self.db=dbTools.loadDB(pth.constants)
self.data=list()
self.dict=dict()
self._headers=1
def load(name):
db =paths.Database()
engineDB =dbTools.loadDB(db.engine)
engineSheet =engineDB.selectByName("ROTAX_912ULS")
eng =pistonEngine(engineSheet,False)
return eng
def load(name):
pth=paths.Database()
acDB =dbTools.loadDB(pth.aircraft)
return Design(acDB.selectByName(name))