def __init__(self):
self.residuals = {'continuity':1e-3,'xvelocity':1e-3,'yvelocity':1e-3,
'energy':1e-6,'nut':1e-3,'k':1e-3,'omega':1e-3,'epsilon':1e-3}
self.relaxationFactor = {'a':0.1}
self.turbulenceInput = {'SA':'no\nno\nyes\nno\n10\n',
'ke-realizable':'no\nno\nyes\n10\n10\n'}
self.residualsInput = {'SA':['continuity','xvelocity','yvelocity','energy','nut'],
'ke-realizable':['continuity','xvelocity','yvelocity','energy','k','epsilon']}
self.turbulenceName = {'SA':'spalart-allmaras','ke-realizable':'ke-realizable'}
self.iterMax = 5000
self.momentAxisPt = [0.25,0]
self.momentAxisVec = [0,0,-1]
self.turbulence = 'SA' #'ke-realizable'
self.paths = CFD_paths()
self.result = AirfoilPolar1D()#FluentOutput()
self._meshtype = 'O'
self.densityBased = True
class FluentAirfoil():
def __init__(self):
self.residuals = {'continuity':1e-3,'xvelocity':1e-3,'yvelocity':1e-3,
'energy':1e-6,'nut':1e-3,'k':1e-3,'omega':1e-3,'epsilon':1e-3}
self.relaxationFactor = {'a':0.1}
self.turbulenceInput = {'SA':'no\nno\nyes\nno\n10\n',
'ke-realizable':'no\nno\nyes\n10\n10\n'}
self.residualsInput = {'SA':['continuity','xvelocity','yvelocity','energy','nut'],
'ke-realizable':['continuity','xvelocity','yvelocity','energy','k','epsilon']}
self.turbulenceName = {'SA':'spalart-allmaras','ke-realizable':'ke-realizable'}
self.iterMax = 5000
self.momentAxisPt = [0.25,0]
self.momentAxisVec = [0,0,-1]
self.turbulence = 'SA' #'ke-realizable'
self.paths = CFD_paths()
self.result = AirfoilPolar1D()#FluentOutput()
self._meshtype = 'O'
self.densityBased = True
def _create_journal_file(self,alpha,flightConditions,caseFilePath=None,turbulenceModel='SA',Cp=False,
journalPath=None,outputDirectory=None):
if self._meshtype=='O':
ffbc = 'bc-3-5'
wallbc = 'bc-2-4'
elif self._meshtype=='C':
ffbc = 'bc-3-4'
wallbc = 'bc-2-5'
if outputDirectory==None:
outputDirectory = self.paths.tmpdir
if journalPath==None:
journalPath = self.paths.file_jou
if caseFilePath==None:
caseFilePath = self.paths.file_cas
self.paths.set_name_alpha(alpha)
freestream = [cos(radians(alpha)), sin(radians(alpha))]
script = open(journalPath,'wt')
script.write('/file/read\n')
script.write('%s\n'%caseFilePath)
script.write('/define/operating-conditions/operating-pressure\n')
script.write('0\n')
script.write('/define/models/viscous/%s\nyes\n'%self.turbulenceName[turbulenceModel])
#if flightConditions.Mach>=0.7:
if self.densityBased:
script.write('/define/models/solver/density-based-implicit\nyes\n')
script.write('/define/materials/change-create\n')
script.write('air\n\nyes\n')
script.write('ideal-gas\n')
script.write('no\nno\nyes\n')
script.write('sutherland\n')
script.write('three-coefficient-method\n')
script.write('1.716e-05\n273.11\n110.56\n')
script.write('no\nno\nno\n')
script.write('/define/boundary-conditions/pressure-far-field/\n')
script.write('%s\n'%ffbc)
script.write('no\n')
script.write('%.2f\n'%flightConditions.atm.pressure)
script.write('no\n%.6f\n'%flightConditions.Mach)
script.write('no\n%.6f\n'%flightConditions.atm.temperature)
script.write('no\n')
script.write('%.10f\n'%freestream[0])
script.write('no\n')
script.write('%.10f\n'%freestream[1])
script.write('%s'%self.turbulenceInput[turbulenceModel])
script.write('/solve/monitors/residual/convergence-criteria\n')
for resid in self.residualsInput[turbulenceModel]:
script.write('%.4e\n'%self.residuals[resid])
script.write('/solve/monitors/force/drag-coefficient\n')
script.write('yes\n%s\n\nno\nyes\n'%wallbc)
script.write('\"%s\"\nno\nno\n'%self.paths.file_cd_hist)
script.write('%.10f\n'%freestream[0])
script.write('%.10f\n'%freestream[1])
script.write('/solve/monitors/force/lift-coefficient\n')
script.write('yes\n%s\n\nno\nyes\n'%wallbc)
script.write('\"%s\"\nno\nno\n'%self.paths.file_cl_hist)
script.write('%.10f\n'%(-freestream[1]))
script.write('%.10f\n'%freestream[0])
script.write('/solve/monitors/force/moment-coefficient\n')
script.write('yes\n%s\n\nno\nyes\n'%wallbc)
script.write('\"%s\"\nno\nno\n'%self.paths.file_cm_hist)
script.write('%.4f\n'%self.momentAxisPt[0])
script.write('%.4f\n'%self.momentAxisPt[1])
script.write('%.4f\n%.4f\n%.4f\n'%(self.momentAxisVec[0],self.momentAxisVec[1],self.momentAxisVec[2]))
script.write('/report/reference-values/compute/pressure-far-field\n%s\n'%ffbc)
script.write('/solve/initialize/compute-defaults/pressure-far-field\n%s\n'%ffbc)
script.write('/solve/iterate\n')
script.write('%d\n'%self.iterMax)
script.write('\nexit\nok\n')
script.close()
def run_at_aoa(self,alpha,flightConditions,caseFilePath=None,
turbulenceModel='SA',Cp=False,iterMax=5000,densityBased=False):
"""
Run Ansys fluent airfoil analysis at single angle of attack
Parameters
----------
alpha : float, deg
angle of attack
flightCondtions : object
flight condtions object
caseFilePath : string
path of the case file with mesh
turbulenceModel : string
two models are available now "SA" and "ke-realizable"
Cp : bool
output Cp distribution. Not available
iterMax : int
maximum number of iterations
"""
self.densityBased = densityBased
self.result.alpha = alpha
self.paths.set_name_alpha(alpha)
self.result.Mach = flightConditions.Mach
self.result.Re = flightConditions.Re
self.iterMax = iterMax
self._create_journal_file(alpha,flightConditions,caseFilePath,turbulenceModel,Cp)
self._run_fluent()
self._collect_output()
return self.result
def _run_fluent(self):
system('\"\"%s\" 2ddp -hidden -i \"%s\"\"'%(self.paths.fluent,self.paths.file_jou))
def _collect_output(self,histFileDir=None,Cp=False):
if histFileDir==None:
histFileDir=self.paths.tmpdir
self._read_history_files(self.paths.list_hist_files)
def _read_history_files(self,listOfHistFilesPath):
result = zeros(3)
for i,histFilePath in enumerate(listOfHistFilesPath):
result[i] = self._read_history_file(histFilePath)
self.result.cl = result[0]
self.result.cd = result[1]
self.result.cm = result[2]
self.result.LD = result[0]/result[1]
def _read_history_file(self,histFilePath):
fid = open(histFilePath,'rt')
line = fid.readlines()[-1]
fid.close()
return float(line.split()[1])
