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 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 _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 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 _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 _readData(self):
"""
reads engine database excel file.
Parameters
----------
gearboxRatio : float
engine gearbox ratio
mass : float, kg
engine mass
length : float, m
engine length
width : float, m
engine width
height : float, m
engine height
flatRateAlt : float, m
engine flat rate altitude
The altitude at which engine performance begins to decrease due to
reducing atmospheric density
RPM : array
array of rpm from db
torque : array
array of torque at rpm
fuelFlow : array
array of fuel flow at rpm
fuelDensity : float
density of fuel for conversion kg/h, l/h
"""
db=dbTools.readDB(self._inputSheet)
self.gearboxRatio =db.readRow(1,1)
self.mass =db.readRow(2,1)
self.length =db.readRow(3,1)
self.width =db.readRow(4,1)
self.height =db.readRow(5,1)
self.flatRateAlt =db.readRow(6,1)
self.RPM =db.readRow(7,1)
self.power =db.readRow(8,1)*1000
self.torque =db.readRow(9,1)
self.fuelFlow =db.readRow(10,1)
self.fuelDensity =db.readRow(11,1)
self.sfc =self.fuelFlow*self.fuelDensity/3600.0/self.power
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 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 _readData(self):
db=dbTools.readDB(self._inputSheet)
# Reading in Design Quantities Section
i=db.findHeader("SECTION: DESIGN QUANTITIES")
self.type =db.readRow(i+1,1)
fuelMass =db.readRow(i+2,1)
designGrossMass =db.readRow(i+3,1)
designSpeed =db.readRow(i+4,1)
designAltitude =db.readRow(i+5,1)
designLoadFactor =db.readRow(i+6,1)
designLandingLoadFactor =db.readRow(i+7,1)
occupantNumber =db.readRow(i+8,1)
payloadMass =db.readRow(i+9,1)
self.designGoals=designGoals(fuelMass,designGrossMass,designSpeed,designAltitude,designLoadFactor,designLandingLoadFactor,occupantNumber,payloadMass)
# Reading in Main Wing Section
i=db.findHeader("SECTION: MAIN WING")
segmentSpans =db.readRow(i+1,1,iterable=True)
chords =db.readRow(i+2,1,iterable=True)
airfoilName =db.readRow(i+3,1,iterable=True)
segmentOffsets =db.readRow(i+4,1,iterable=True)
segmentDihedrals =db.readRow(i+5,1,iterable=True)
twistAngles =numpy.concatenate((numpy.zeros(1),db.readRow(i+6,1,iterable=True)))
incidence =db.readRow(i+7,1)
aapex =db.readRow(i+8,1)
aileronLocation =db.readRow(i+9,1)
flapLocation =db.readRow(i+10,1)
flapType =db.readRow(i+11,1)
fuelWingCG =db.readRow(i+12,1)
material =db.readRow(i+13,1)
self.wing=wing(segmentSpans,chords,airfoilName,segmentOffsets,
segmentDihedrals,twistAngles,incidence,aapex,material,1)
self.wing.setFuelTank(fuelMass/2.0,1,fuelWingCG[0],fuelWingCG[1])
self.wing.addAileron(aileronLocation)
self.wing.addFlap(flapLocation,flapType)
# Reading in Horizontal Stab Section
i=db.findHeader("SECTION: HORIZONTAL STABILIZER")
segmentLengths =db.readRow(i+1,1,iterable=True)
chords =db.readRow(i+2,1,iterable=True)
airfoilName =db.readRow(i+3,1,iterable=True)
segmentOffsets =db.readRow(i+4,1,iterable=True)
segmentDihedrals =db.readRow(i+5,1,iterable=True)
twistAngles =numpy.zeros(len(chords))
incidence =db.readRow(i+6,1)
aapex =db.readRow(i+7,1)
elevatorLocation =db.readRow(i+8,1)
material =db.readRow(i+8,1)
#self.hStab=hStab(segmentLengths,chords,airfoilName,segmentOffsets,segmentDihedrals,incidence,aapex,elevatorLocation,material)
self.hStab=wing(segmentLengths,chords,airfoilName,segmentOffsets,segmentDihedrals,twistAngles,incidence,aapex,material,1,False)
self.hStab.addElevator(elevatorLocation)
# Reading in Vertical Stab Section
i=db.findHeader("SECTION: VERTICAL STABILIZER")
number =db.readRow(i+1,1)
lateralDistance =db.readRow(i+2,1)
segmentLengths =db.readRow(i+3,1,iterable=True)
chords =db.readRow(i+4,1,iterable=True)
airfoilName =db.readRow(i+5,1,iterable=True)
segmentOffsets =db.readRow(i+6,1,iterable=True)
segmentDihedrals =db.readRow(i+7,1,iterable=True)
twistAngles =numpy.zeros(len(chords))
aapex =db.readRow(i+8,1)
rudderLocation =db.readRow(i+9,1)
material =db.readRow(i+10,1)
self.vStab=wing(segmentLengths,chords,airfoilName,segmentOffsets,segmentDihedrals,twistAngles,incidence,aapex,material,0,True)
self.vStab.addRudder(rudderLocation)
self.vStabNum =number
self.vStabSeparation =lateralDistance
# Reading in Fuselage Data
i=db.findHeader("SECTION: FUSELAGE")
length =db.readRow(i+1,1)
diameter =db.readRow(i+2,1)
wettedArea =db.readRow(i+3,1)
sideProfile_X =db.readRow(i+4,1)
sideProfile_Y =db.readRow(i+5,1)
topProfile_X =db.readRow(i+6,1)
topProfile_Y =db.readRow(i+7,1)
material =db.readRow(i+8,1)
self.fuselage=fuselage(length,diameter,wettedArea,sideProfile_X,sideProfile_Y,topProfile_X,topProfile_Y,material)
# Reading in Engine Data
i=db.findHeader("SECTION: PROPULSION")
name =db.readRow(i+1,1)
CG_X =db.readRowAsArray(i+2,1)
CG_Y =db.readRowAsArray(i+3,1)
CG_Z =db.readRowAsArray(i+4,1)
propName =db.readRow(i+5,1)
propHub_X =db.readRowAsArray(i+6,1)
propHub_Y =db.readRowAsArray(i+7,1)
propHub_Z =db.readRowAsArray(i+8,1)
minBeta =db.readRowAsArray(i+9,1)
maxBeta =db.readRowAsArray(i+10,1)
self.engine=engine(name,CG_X,CG_Y,CG_Z)
self.propeller=propeller(propName,propHub_X,propHub_Y,propHub_Z,minBeta,maxBeta)
# Reading in Landing Gear Data
i=db.findHeader("SECTION: LANDING GEAR")
gearType =db.readRow(i+1,1)
tireWidth =db.readRow(i+2,1)
tireDiameter =db.readRow(i+3,1)
strutLength =db.readRow(i+4,1)
strutType =db.readRow(i+5,1)
fairingType =db.readRow(i+6,1)
groundContact_X =db.readRow(i+7,1)
groundContact_Y =db.readRow(i+8,1)
groundContact_Z =db.readRow(i+9,1)
self.landingGear=landingGear(gearType,tireWidth,tireDiameter,strutLength,strutType,fairingType,groundContact_X,groundContact_Y,groundContact_Z)
# Reading in VLM Operating Parameters
i=db.findHeader("SECTION: OPTIONAL VLM PARAMS")
defaultFlag =int(db.readRow(i+1,1))
if defaultFlag==1:
wing_spanwise =db.readRow(i+2,1)
wing_chordwise =db.readRow(i+3,1)
hStab_spanwise =db.readRow(i+4,1)
hStab_chordwise =db.readRow(i+5,1)
vStab_spanwise =db.readRow(i+6,1)
vStab_chordwise =db.readRow(i+7,1)
cosDistribution =db.readRow(i+8,1)
sinDistribution =db.readRow(i+9,1)
self.VLMsetup=VLMsetup(wing_spanwise,wing_chordwise,hStab_spanwise,hStab_chordwise,vStab_spanwise,vStab_chordwise,cosDistribution,sinDistribution)
else:
self.VLMsetup=VLMsetup()
# Reading in Mass List
massSec=db.read_section('MASS SOURCES',0)
self.mass = weight.AircraftMass(self.name)
for line in massSec:
name=str(line[0])
values =numpy.array(line[1:])
mass =values[0]
CG =values[1:4]
MOM =values[5:8]
self.mass.payload.add_item(name,mass,CG,MOM)
self.mass.fuel.add_item('Fuel tank Right',fuelMass/2.0)
self.mass.fuel.add_item('Fuel tank Left',fuelMass/2.0)
self.mass.update_total()
# Reading in Drag List
dragSec=db.read_section('DRAG SOURCES',0)
self.drag = drag.AircraftDrag()
# self.drag=drag.DragList()
for line in dragSec:
drg=drag.DragItem()
drg.name=str(line[0])
drg.quantity=int(line[1])
drg.frontArea=float(line[2])
self.drag.components.add_item(drg)