def run_test1():
import aircraft_FW
ac = aircraft_FW.load('X47B')
print ac.designGoals.fuelMass
print ac.get_mass_fuel()
ac.get_mission_fuel()
print ac.designGoals.fuelMass
print ac.get_mass_fuel()
#ac.display()
slf =SteadyLevelFlight(ac)
#alt = ac.designGoals.cruiseAltitude
alt = 1e4
print 'MAXIMUM SPEED'
print slf.run_max_TAS(alt)
print 'MINIMUM SPEED'
print slf.run_min_TAS(alt)
print 'MAXIMUM SAR'
print slf.run_max_SAR(alt)
print 'MINIMUM FUEL'
print slf.run_min_fuel(alt)
ac.mass.fuel.set_fuel_fraction(0.5)
clm = ClimbDescent(ac)
print 'MAXIMUM CLIMB RATE'
print clm.run_max_climb_rate(0)
print 'MOST ECONOMICAL CLIMB'
print clm.run_most_economical_climb(0)
print 'SERVICE CEILING'
print clm.get_service_ceiling()
print 'ABSOLUTE CEILING'
print clm.get_absolute_ceiling()
def run_mission_B11(ac=None):
""" maximum cruise range """
if ac==None:
ac = aircraft_FW.load('X45C')
#ac.mass.payload.remove_item('drop payload')
slf = Cruise(ac)
clm = Climb(ac)
# -- mission inputs --
altField = 0.0
altCruise = 1.0e4
timeReserve = 1800.0 # 30min
Wf0 = ac.mass.fuel.mass
# -- assumptions --
fuelReserveStart = 0.1*Wf0
# climb
climb1 = clm.run_climb(altField, altCruise,Wf0)
#climb1.display('Climb 1')
# reserve fuel
reserve = slf.run_maximum_endurance_fuel(altField,fuelReserveStart,timeReserve)
#reserve.display('Reserve')
WfReserve = reserve.fuelBurned + 0.05*Wf0
# cruise
Wfcrs = Wf0 - climb1.fuelBurned
cruise = slf.run_maximum_range(altCruise,Wfcrs,WfReserve)
#cruise.display('Cruise')
Range = climb1.distance + cruise.distance
#print Range/1e3
return Range
def create_input_files2():
import aircraft_FW
ac = aircraft_FW.load('aeroValidation',False)
name = 'aeroValidation'
CG = [0.2,0,0]
yplus = .5
wdir = 'D:\sync_Maxim'
alpha = [0,2,4,8,12]
niter = 5000
batFile = 'run_cfd_batch2.bat'
pathFluent = r'C:\Program Files\Ansys Inc\v130\fluent\ntbin\win64\fluent.exe'
igsPath = '%s.igs'%name
symCasPath = '%s_sym.cas'%name
nonsymCasPath = '%s_half.cas'%name
glfPath = '%s.glf'%name
create_fw_cmesh(ac,igsPath,symCasPath,nonsymCasPath,yplus,glfPath)
Sref = ac.wing.area/2.0
Cref = ac.wing.MAC
fid = open(batFile,'wt')
for a in alpha:
outPrefix = '%s\\results\\%s_half_a%d'%(wdir,name,a*100)
journalFileRel = '%s_half_a%d.jou'%(name, a*100)
journalFile = '%s_half_a%d.jou'%(name, a*100)
run_wing_half(nonsymCasPath, outPrefix, ac.designGoals.fc, a, 0,
Sref, Cref, CG, journalFile,niter)
fid.write('\"%s\" 3ddp -t8 -i %s -wait\n'%(pathFluent, journalFileRel))
fid.close()
def climb_test():
import aircraft_FW
ac = aircraft_FW.load('X47B')
clm = Climb(ac)
results = clm.run_climb2(0,1e4,0.3,0.7)
results.display()
results2 = clm.run_climb(0,1e4)
results2.display()
def run_test1():
ac = aircraft_FW.load('X45C')
#bi = BasicInput(ac)
fm = FlightMechanics(ac)
print fm.get_Vstall()
print fm.get_EAS(100.,1.0)
print fm.get_LDmax()
print fm.get_V_LDmax()
print fm.get_required_thrust(100,1e4)
def run_test1():
import aircraft_FW
ac = aircraft_FW.load('Baseline1')
print ac.get_mission_fuel()
to = Takeoff(ac,0)
print to.analyze()
ldg = Landing(ac,0)
print ldg.analyze()
def run_test1():
import aircraft_FW as aircraft
ac = aircraft.load('Baseline1')
aero = Aerodynamics(ac)
fc = FlightConditionsAVL(ac,0.5,1e4)
#results = aero.run_trim(fc)
#results.display()
results2 = aero.run_single_point(fc,0.0,2.0)
results2.display()
def run_test2():
import matplotlib.pyplot as plt
import numpy as np
ac = aircraft_FW.load('X45C')
#bi = BasicInput(ac)
fm = FlightMechanics(ac)
V = np.linspace(100,400,50)
Treq = np.array([fm.get_required_thrust(v,10000)/1e3 for v in V])
plt.figure()
plt.plot(V,Treq)
plt.show()
def run_mission_B15(ac=None):
""" air assault mission """
if ac==None:
import aircraft_FW
ac = aircraft_FW.load('X45C')
#ac.display()
# -- mission inputs --
altField = 0.0
altCruise = 1.0e4
altAttack = convert.ft_to_m(2000)
distAttack = convert.nm_to_m(200)
timeReserve = 1800.0 # 30min
speedMaxAttack = convert.kt_to_msec(360)
Wf0 = ac.mass.fuel.mass
# -- assumptions --
fuelReserveStart = 0.1*Wf0
fuelAttackStart = 0.5*Wf0
# -- calculations --
slf = Cruise(ac)
clm = Climb(ac)
# reserve fuel
reserve = slf.run_maximum_endurance_fuel(altField,fuelReserveStart,timeReserve)
WfReserve = reserve.fuelBurned + 0.05*Wf0
# climb 1
climb1 = clm.run_climb(altField, altCruise,Wf0)
# penetration-withdrawal
penetration = slf.run_distance_at_speed(altAttack,speedMaxAttack,distAttack,fuelAttackStart)
slf.drop_payload()
withdrawal = slf.run_distance_at_speed(altAttack,speedMaxAttack,distAttack,penetration.fuelEnd)
# climb 2
#clm.drop_payload()
climb2 = clm.run_climb(altAttack,altCruise,withdrawal.fuelEnd)
# maximum range
Wfcrs = Wf0 - climb1.fuelBurned - penetration.fuelBurned - withdrawal.fuelBurned
Wfcrs += - climb2.fuelBurned
cruise = slf.run_maximum_range(altCruise,Wfcrs,WfReserve)
# operational range
operRange = climb1.distance + cruise.distance + penetration.distance
operRange += withdrawal.distance + climb2.distance
operRange *= 0.5
return operRange
def run_integrated_analysis(name=None, outputFile=None,detailedReport=True):
if name==None:
name = 'X47B'
#name = str(raw_input('Enter aircraft name:\n'))
if outputFile==None:
outputFile = 'analysisReport_detailed.txt'
#outputFile = str(raw_input('Enter output report textfile name:\n'))
# initialize aircraft and report output
report = db_tools.TextReport()
report.write_line('%s aircraft integrated analysis output'%name)
report.write_Header(str(datetime.datetime.now()))
report.write_newline(2)
ac = aircraft_FW.load(name)
# mission fuel
report.write_header_in_quotes('mission fuel')
reportMis = get_mission_analysis_report(ac)
report.write(reportMis)
report.write_newline(2)
# weight and balance
report.write_header_in_quotes('weight and balance')
reportWB = get_weight_report(ac,detailedReport)
report.write(reportWB)
report.write_newline(2)
report.write_header_in_quotes('stability and control')
reportSnC = get_stability_report(ac)
report.write(reportSnC)
report.write_newline(2)
report.write_header_in_quotes('performance')
reportPerf = get_performance_report(ac,detailedReport)
reportPerf2 = get_max_range(ac)
reportPerf3 = get_max_endurance(ac)
report.write(reportPerf)
report.write('\nMISSION PERFORMANCE\n'+'='*40+'\n')
report.write(reportPerf2)
report.write(reportPerf3)
report.write('\nFIELD PERFORMANCE\n'+'='*40+'\n')
reportField = field_performance_analysis(ac,detailedReport)
report.write(reportField)
report.save_to_file(outputFile,'wt')
display_text_contents(outputFile)
def run_test1():
import aircraft_FW
ac = aircraft_FW.load('X47B')
ac.set_drag_method(0)
#ac.display()
slf =SteadyLevelFlight(ac)
#alt = ac.designGoals.cruiseAltitude
alt = 10000.
print 'MAXIMUM SPEED'
print slf.run_max_TAS(alt)
print 'MINIMUM SPEED'
print slf.run_min_TAS(alt)
print 'MAXIMUM SAR'
print slf.run_max_SAR(alt)
print 'MINIMUM FUEL'
print slf.run_min_fuel(alt)
clm = ClimbDescent(ac)
print 'MAXIMUM CLIMB RATE'
print clm.run_max_climb_rate(0)
print 'ECONOMICAL CLIMB'
print clm.run_most_economical_climb(0)
def run_test1():
import aircraft_FW
ac = aircraft_FW.load('Baseline1')
print get_parasite_drag_fw(ac)
# penetration-withdrawal
penetration = slf.run_distance_at_speed(altAttack,speedMaxAttack,distAttack,fuelAttackStart)
slf.drop_payload()
withdrawal = slf.run_distance_at_speed(altAttack,speedMaxAttack,distAttack,penetration.fuelEnd)
# climb 2
#clm.drop_payload()
climb2 = clm.run_climb(altAttack,altCruise,withdrawal.fuelEnd)
# maximum range
Wfcrs = Wf0 - climb1.fuelBurned - penetration.fuelBurned - withdrawal.fuelBurned
Wfcrs += - climb2.fuelBurned
cruise = slf.run_maximum_range(altCruise,Wfcrs,WfReserve)
# operational range
operRange = climb1.distance + cruise.distance + penetration.distance
operRange += withdrawal.distance + climb2.distance
operRange *= 0.5
return operRange
if __name__=="__main__":
name = 'X45C'
ac = aircraft_FW.load(name)
print run_mission_B15(ac)/1e3
ac = aircraft_FW.load(name)
print run_mission_B11(ac)/1e3
ac = aircraft_FW.load(name)
print run_mission_B10(ac)/1e3
return 0.0
def set_flight_conditions(self,velocity,altitude):
"""
setting flight conditions to be analyzed. Flight conditions are calculated
using FlightConditions module. Reynolds number is calculated using ref
length 1.0 that is stored in self.Re1
"""
self.fc = FlightConditions(velocity,altitude)
self.Re1 = self.fc.Re # Re for L=1
if __name__=="__main__":
import aircraft_FW
import matplotlib.pyplot as plt
ac = aircraft_FW.load('X45C')
wd = WaveDrag(ac.wing)
fd = Friction(ac.wing.area)
M = np.arange(0.1,1.01,0.01)
cd = np.zeros(len(M))
for i,mach in enumerate(M):
fd.set_flight_conditions(mach,10000)
item = fd.analyze_wing(ac.wing,'main wing')
cdf = item.CDtotal
cdw = wd.analyze_wing(mach)
cd[i] = cdw + cdf
#print '%.4f\t%.6f\t%.6f'%(mach,cdw,cdf)
plt.figure(1)
plt.grid(True)
plt.plot(M,cd,'b-')
plt.xlabel('Mach')
print ac.get_mass_fuel()
#ac.display()
slf =SteadyLevelFlight(ac)
#alt = ac.designGoals.cruiseAltitude
alt = 1e4
print 'MAXIMUM SPEED'
print slf.run_max_TAS(alt)
print 'MINIMUM SPEED'
print slf.run_min_TAS(alt)
print 'MAXIMUM SAR'
print slf.run_max_SAR(alt)
print 'MINIMUM FUEL'
print slf.run_min_fuel(alt)
ac.mass.fuel.set_fuel_fraction(0.5)
clm = ClimbDescent(ac)
print 'MAXIMUM CLIMB RATE'
print clm.run_max_climb_rate(0)
print 'MOST ECONOMICAL CLIMB'
print clm.run_most_economical_climb(0)
print 'SERVICE CEILING'
print clm.get_service_ceiling()
print 'ABSOLUTE CEILING'
print clm.get_absolute_ceiling()
if __name__=="__main__":
import aircraft_FW
ac = aircraft_FW.load('X47B')
point_performance_analysis(ac,0.0, None)
def run_test1():
import aircraft_FW
ac = aircraft_FW.load('X47B')
print run_mission_B11(ac)/1e3
def create_wing_db(ac=None, glfPath=None):
if ac==None:
ac = aircraft_FW.load('Baseline1')
if glfPath==None:
glfPath='tmp_glf1.glf'
def get_section_data(wing, idx):
ptsUp = wing.airfoils[idx].ptsUp
ptsLo = wing.airfoils[idx].ptsLo
apex = wing.secApex[idx]
chord = wing.chords[idx]
angle = wing.secAngles[idx]
return ptsUp, ptsLo, apex, chord, angle
def write_curve(fid1, nConnect, pts, apex, chord, angle, rotAxis=0.25, rev=False):
if rev:
pts = np.flipud(pts)
apex = np.array([apex[0],apex[2],apex[1]])
pts = rotate_2d(pts, [rotAxis,0], angle) *chord
pts = np.hstack([pts,np.zeros([len(pts),1])])
pts += apex
for pt in pts:
fid1.write(' $_TMP(PW_%d) addPoint {%.10f %.10f %.10f}\n'%(nConnect,pt[0], pt[1], pt[2]))
fid = open(glfPath,'wt')
fid.write('# Pointwise automation by Maxim Tyan 2014\n')
fid.write('package require PWI_Glyph 2.17.2\n')
fid.write('pw::Application setUndoMaximumLevels 5\n')
fid.write('pw::Application reset\n')
fid.write('pw::Application markUndoLevel {Journal Reset}\n')
fid.write('pw::Application clearModified\n')
fid.write('set _TMP(mode_1) [pw::Application begin Create]\n')
fid.write(' set _TMP(PW_1) [pw::SegmentSpline create]\n')
# 1st segment
ptsUp, ptsLo, apex, chord, angle = get_section_data(ac.wing, 0)
write_curve(fid, 1, ptsUp, apex, chord, angle,rev=True)
fid.write(' $_TMP(PW_1) setSlope Akima\n')
fid.write(' set _TMP(curve_1) [pw::Curve create]\n')
fid.write(' $_TMP(curve_1) addSegment $_TMP(PW_1)\n')
fid.write(' unset _TMP(PW_1)\n')
fid.write('$_TMP(mode_1) end\n')
fid.write('unset _TMP(mode_1)\n')
fid.write('pw::Application markUndoLevel {Create Curve}\n')
fid.write('unset _TMP(curve_1)\n')
fid.write('set _TMP(mode_2) [pw::Application begin Create]\n')
fid.write(' set _TMP(PW_2) [pw::SegmentSpline create]\n')
fid.write(' set _DB(1) [pw::DatabaseEntity getByName "curve-1"]\n')
fid.write(' $_TMP(PW_2) addPoint [list 1 0 $_DB(1)]\n')
write_curve(fid, 2, ptsLo[1:-1], apex, chord, angle)
fid.write(' $_TMP(PW_2) addPoint [list 0 0 $_DB(1)]\n')
fid.write(' $_TMP(PW_2) setSlope Akima\n')
fid.write(' set _TMP(curve_1) [pw::Curve create]\n')
fid.write(' $_TMP(curve_1) addSegment $_TMP(PW_2)\n')
fid.write(' unset _TMP(PW_2)\n')
fid.write('$_TMP(mode_2) end\n')
fid.write('unset _TMP(mode_2)\n')
fid.write('pw::Application markUndoLevel {Create Curve}\n')
# 2nd segment
fid.write('unset _TMP(curve_1)\n')
fid.write('set _TMP(mode_3) [pw::Application begin Create]\n')
fid.write(' set _TMP(PW_3) [pw::SegmentSpline create]\n')
ptsUp, ptsLo, apex, chord, angle = get_section_data(ac.wing, 1)
write_curve(fid, 3, ptsUp, apex, chord, angle)
fid.write(' $_TMP(PW_3) setSlope Akima\n')
fid.write(' set _TMP(curve_1) [pw::Curve create]\n')
fid.write(' $_TMP(curve_1) addSegment $_TMP(PW_3)\n')
fid.write(' unset _TMP(PW_3)\n')
fid.write('$_TMP(mode_3) end\n')
fid.write('unset _TMP(mode_3)\n')
fid.write('pw::Application markUndoLevel {Create Curve}\n')
fid.write('unset _TMP(curve_1)\n')
fid.write('set _TMP(mode_4) [pw::Application begin Create]\n')
fid.write(' set _TMP(PW_4) [pw::SegmentSpline create]\n')
fid.write(' set _DB(2) [pw::DatabaseEntity getByName "curve-3"]\n')
fid.write(' $_TMP(PW_4) addPoint [list 0 0 $_DB(2)]\n')
write_curve(fid, 4, ptsLo[1:-1], apex, chord, angle)
fid.write(' $_TMP(PW_4) addPoint [list 1 0 $_DB(2)]\n')
fid.write(' $_TMP(PW_4) setSlope Akima\n')
fid.write(' set _TMP(curve_1) [pw::Curve create]\n')
fid.write(' $_TMP(curve_1) addSegment $_TMP(PW_4)\n')
fid.write(' unset _TMP(PW_4)\n')
fid.write('$_TMP(mode_4) end\n')
fid.write('unset _TMP(mode_4)\n')
fid.write('pw::Application markUndoLevel {Create Curve}\n')
fid.write('unset _TMP(curve_1)\n')
fid.write(' set _TMP(mode_5) [pw::Application begin Create]\n')
fid.write(' set _TMP(PW_5) [pw::SegmentSpline create]\n')
# tip
ptsUp, ptsLo, apex, chord, angle = get_section_data(ac.wing, 2)
write_curve(fid, 5, ptsUp, apex, chord, angle)
fid.write(' $_TMP(PW_5) setSlope Akima\n')
fid.write(' set _TMP(curve_1) [pw::Curve create]\n')
fid.write(' $_TMP(curve_1) addSegment $_TMP(PW_5)\n')
fid.write(' unset _TMP(PW_5)\n')
fid.write('$_TMP(mode_5) end\n')
fid.write('unset _TMP(mode_5)\n')
fid.write('pw::Application markUndoLevel {Create Curve}\n')
fid.write('unset _TMP(curve_1)\n')
fid.write('set _TMP(mode_6) [pw::Application begin Create]\n')
fid.write(' set _TMP(PW_6) [pw::SegmentSpline create]\n')
fid.write(' set _DB(3) [pw::DatabaseEntity getByName "curve-5"]\n')
fid.write(' $_TMP(PW_6) addPoint [list 1 0 $_DB(3)]\n')
write_curve(fid, 6, ptsLo[1:-1], apex, chord, angle,rev=True)
fid.write('$_TMP(PW_6) addPoint [list 0 0 $_DB(3)]\n')
fid.write('$_TMP(PW_6) setSlope Akima\n')
fid.write('set _TMP(curve_1) [pw::Curve create]\n')
fid.write('$_TMP(curve_1) addSegment $_TMP(PW_6)\n')
fid.write('unset _TMP(PW_6)\n')
fid.write('$_TMP(mode_6) end\n')
fid.write('unset _TMP(mode_6)\n')
fid.write('pw::Application markUndoLevel {Create Curve}\n')
fid2 = open('./templates/fw_db_automation_surface.txt','rt')
for line in fid2:
fid.write(line)
fid2.close()
fid.close()
def create_fw_cmesh(ac=None,igsPath=None,casPathSym=None, casPathNonsym=None, yplus=.5,
glfPath=None):
if ac==None:
ac = aircraft_FW.load('Baseline1')
if igsPath==None:
igsPath = r'E:/1. Current work/2014 - UAV performance code/CFD automation/fw3.igs'
if casPathSym==None:
casPathSym = 'fw_case_sym.cas'
if casPathNonsym==None:
casPathNonsym = 'fw_case_nonsym.cas'
if glfPath==None:
glfPath='dbg_cmesh.glf'
create_wing_db(ac,glfPath)
fid = open('./templates/fw_automation.glf')
lines = fid.readlines()
fid.close()
#print ac.get_cg()
nWallChord = 65
nWallSeg1 = 30
nWallSeg2 = 31
nWallTip = 8
nFFx = 46
nFFy = 75
nFFz = 46
#yplus = 0.5
dsLE = 2e-3
dsFFy = 1e-3
dsTopAft = 1e-2
dsTopFront = 1e-2
dsZ = 1e-3
# igs input file
#lines[14] = ' $_TMP(mode_1) initialize -type Automatic {%s}\n'%igsPath
# wing tip
tc = ac.wing.airfoils[-1].thickness
tc *= ac.wing.chords[-1] / 2.
sweep = ac.wing.segSweepLErad[-1] + np.radians(5)
pt1offset = np.array([tc*np.tan(sweep), 0, tc])
pt2offset = np.array([0, 0, tc])
create_wing_db(ac,glfPath)
dl = 34
lines[40-dl] = ' $_TMP(PW_2) addPoint [pwu::Vector3 add [pw::Application getXYZ [$_CN(1) getPosition -arc 0]] {%.6f %.6f %.6f}]\n'%(pt1offset[0], pt1offset[1],pt1offset[2])
lines[53-dl] = ' $_TMP(PW_3) addPoint [pwu::Vector3 add [pw::Application getXYZ [$_CN(1) getPosition -arc 1]] {%.6f %.6f %.6f}]\n'%(pt2offset[0], pt2offset[1],pt2offset[2])
# ff aft
span = ac.wing.span + tc
lines[186-dl] = ' $_TMP(PW_13) addPoint [pwu::Vector3 add [$_CN(11) getPosition -arc 1] {0 0 %.6f}]\n'%span
lines[198-dl] = ' $_TMP(PW_14) addPoint [pwu::Vector3 add [$_CN(13) getPosition -arc 1] {0 0 %.6f}]\n'%span
lines[211-dl] = ' $_TMP(PW_15) addPoint [pwu::Vector3 add [$_CN(12) getPosition -arc 1] {0 0 %.6f}]\n'%span
# number of points
lines[380-dl] = '$_TMP(PW_28) do setDimension %d\n'%nWallChord
lines[387-dl] = '$_TMP(PW_29) do setDimension %d\n'%nWallSeg1
lines[394-dl] = '$_TMP(PW_30) do setDimension %d\n'%nWallSeg2
lines[401-dl] = '$_TMP(PW_31) do setDimension %d\n'%nWallTip
lines[408-dl] = '$_TMP(PW_32) do setDimension %d\n'%(nWallSeg1+nWallSeg2+nWallTip-2)
lines[416-dl] = '$_TMP(PW_33) do setDimension %d\n'%nFFx
lines[424-dl] = '$_TMP(PW_34) do setDimension %d\n'%nFFy
lines[432-dl] = '$_TMP(PW_35) do setDimension %d\n'%nFFz
lines[439-dl] = '$_TMP(PW_36) do setDimension %d\n'%(2*nWallChord-1)
lines[446-dl] = '$_TMP(PW_37) do setDimension %d\n'%nFFz
# wall spacing BL
ds1 = ac.designGoals.fc.get_wall_spacing(yplus)
cr = ac.wing.chords[0]
ct = ac.wing.chords[-1]
#FIXME: high taper ratio caused negative jacobean, so it is decided
# temporarily assume yplus at MAC for all wing
cr = ac.wing.MAC
ct = ac.wing.MAC
lines[453-dl] = ' $_TMP(PW_38) setBeginSpacing %.6e\n'%(ds1*cr)
lines[456-dl] = ' $_TMP(PW_39) setBeginSpacing %.6e\n'%(ds1*cr)
lines[464-dl] = ' $_TMP(PW_40) setBeginSpacing %.6e\n'%(ds1*ct)
lines[467-dl] = ' $_TMP(PW_41) setBeginSpacing %.6e\n'%(ds1*ct)
# leading/trailing edge spacing
c2 = ac.wing.chords[1]
dsLEr = dsLE*cr
dsLE2 = dsLE*c2
dsLEt = dsLE*ct
lines[551-dl] = ' $_TMP(PW_59) setBeginSpacing %.10f\n'%(dsLEr)
lines[554-dl] = ' $_TMP(PW_60) setEndSpacing %.10f\n'%(dsLEr)
lines[557-dl] = ' $_TMP(PW_61) setBeginSpacing %.10f\n'%(dsLEr)
lines[560-dl] = ' $_TMP(PW_62) setEndSpacing %.10f\n'%(dsLEr)
lines[568-dl] = ' $_TMP(PW_63) setBeginSpacing %.10f\n'%(dsLE2)
lines[571-dl] = ' $_TMP(PW_64) setEndSpacing %.10f\n'%(dsLE2)
lines[574-dl] = ' $_TMP(PW_65) setBeginSpacing %.10f\n'%(dsLE2)
lines[577-dl] = ' $_TMP(PW_66) setEndSpacing %.10f\n'%(dsLE2)
lines[585-dl] = ' $_TMP(PW_67) setBeginSpacing %.10f\n'%(dsLEt)
lines[588-dl] = ' $_TMP(PW_68) setEndSpacing %.10f\n'%(dsLEt)
lines[591-dl] = ' $_TMP(PW_69) setBeginSpacing %.10f\n'%(dsLEt)
lines[594-dl] = ' $_TMP(PW_70) setEndSpacing %.10f\n'%(dsLEt)
lines[597-dl] = ' $_TMP(PW_71) setBeginSpacing %.10f\n'%(dsLEt)
lines[600-dl] = ' $_TMP(PW_72) setEndSpacing %.10f\n'%(dsLEt)
lines[608-dl] = ' $_TMP(PW_73) setEndSpacing %.10f\n'%(dsLEt)
# case file export
lines[1089] = ' $_TMP(mode_1) initialize -type CAE {%s}\n'%casPathNonsym
lines[1113] = ' $_TMP(mode_4) initialize -type CAE {%s}\n'%casPathSym
#glfPath = os.path.abspath('temp/new.glf')
fid = open(glfPath,'at')
for line in lines:
fid.write(line)
fid.close()
#print glfPath
os.system('\"%s\"'%glfPath)
