def run_test1():
#xdoe = np.array([[0.,0],[0,0.5],[0,1],[0.5,0],[0.5,0.5],[0.5,1],[1.,0],[1.,0.5],[1,1]])
xdoe = read_tabulated_data_without_header('LHC9_2.txt')
ffd = read_tabulated_data_without_header('ffd5_2.txt')
ffd = (ffd-1)/4.0
xdoe = (xdoe+1.0)/2.
fdoe = [func(xx) for xx in xdoe]
newfunc = Function(func)
err1,errSq1 = newfunc(xdoe)
fitness = get_fitness(err1)
xnew = np.zeros(xdoe.shape)
for i in range(4):
idx1 = selection(fitness)
idx2 = selection(fitness,idx1)
xnew[2*i],xnew[2*i+1] = cross_over(xdoe[idx1],xdoe[idx2])
idx1 = selection(fitness)
idx2 = selection(fitness,idx1)
xnew[-1],_t = cross_over(xdoe[idx1],xdoe[idx2])
fnew = [func(xx) for xx in xnew]
xnew1 = np.vstack([xdoe,xnew])
fnew1 = [func(xx) for xx in xnew1]
err,errSq2 = newfunc(xnew1)
print errSq1, errSq2
xrand = read_tabulated_data_without_header('LHC18_2.txt')
xrand = (xrand+1.0)/2.
#xrand = np.random.random([18,2])
frand = [func(xx) for xx in xrand]
print newfunc(xrand)[1]
model1 = RbfMod(xnew1,fnew1)
model2 = RbfMod(xrand,frand)
print calc_error(func,model1,ffd)
print calc_error(func,model2,ffd)
lb = np.array([0,0.])
ub = np.array([1.,1])
n = 40
xs = ys = np.linspace(lb[0],ub[0],n)
X, Y = np.meshgrid(xs,ys)
zs1 = np.array([func([xs,ys]) for xs,ys in zip(np.ravel(X),np.ravel(Y))])
Z1 = zs1.reshape(X.shape)
zs2 = np.array([model1([xs,ys]) for xs,ys in zip(np.ravel(X),np.ravel(Y))])
Z2 = zs2.reshape(X.shape)
zs3 = np.array([model2([xs,ys]) for xs,ys in zip(np.ravel(X),np.ravel(Y))])
Z3 = zs3.reshape(X.shape)
fig2 = plt.figure(1)
ax2 = Axes3D(fig2)
ax2.hold(True)
ax2.plot_wireframe(X,Y,Z1,color='b')
ax2.plot_wireframe(X,Y,Z2,color='r')
ax2.plot_wireframe(X,Y,Z3,color='y')
ax2.plot(xdoe[:,0],xdoe[:,1],fdoe,'ro')
ax2.plot(xnew[:,0],xnew[:,1],fnew,'go')
#ax2.plot(xdoe[:,0],xdoe[:,1],err1,'ko')
ax2.plot(xrand[:,0],xrand[:,1],frand,'bo')
ax2.legend(['High fidelity function','Low fidelity function'])
ax2.set_xlabel('x1')
ax2.set_ylabel('x2')
ax2.set_zlabel('f (x1,x2)')
plt.show()
def calculate_scaling_factors():
def process_cd0(CL0=-.1,f=None):
if f.ndim==2:
CD1 = f[:,1]
CD2 = f[:,4]
CL1 = f[:,0]
CL2 = f[:,3]
else:
CD1 = f[1]
CD2 = f[4]
CL1 = f[0]
CL2 = f[3]
tmp1 = (CL1-CL0)**2.
tmp2 = (CL2-CL0)**2.
k = (CD1 - CD2)/(tmp1 - tmp2)
CD0 = CD1 - k*CL1*CL1
return CD0, k
def adjust_cd0(f,cd0avl,kavl):
bnds = ((-.1,.1),)
def obj(x,f):
cd0,k = process_cd0(x,f)
return 1e4*(cd0-cd0avl)**2.0 + (k-kavl)**2.0
cl0 = fmin_slsqp(obj,[0],bounds=bnds,args=(f,))[0]
cd0,k = process_cd0(cl0,f)
return cd0,k,cl0
xpath = r'E:\1. Current work\2014 - UAV performance code\Results\DOE\LHS_dvar9_sample24.txt'
fpath = r'E:\1. Current work\2014 - UAV performance code\Results\DOE\CFD_FW_results-longitudinal2.txt'
out = r'E:\1. Current work\2014 - UAV performance code\Results\DOE\CFD_FW_results-longitudinal3.txt'
ac = DesignFormulation()
ac.load_xls('Baseline1')
ac.setup()
xData = read_tabulated_data_without_header(xpath)
fData = read_tabulated_data_without_header(fpath,1)
k = np.zeros(fData.shape[0])
CD0 = np.zeros(fData.shape[0])
#CD0cfd, kcfd = process_cd0(f=fData)
fid = open(out,'wt')
fid.write('CD0avl\tkavl\tCD0cfd\tkcfd\tCD0add\tkadd\tCL0\n')
for i,x in enumerate(xData):
ac.set_x(x)
aero = ac.get_aero_single_point(.7,1e4,alpha=2.)
k[i] = aero.k
CD0[i] = aero.CD0
CD0cfd,kcfd,cl0 = adjust_cd0(fData[i],CD0[i],k[i])
print CD0cfd, kcfd, cl0
print 'case ',i
fid.write('%.9f\t%.9f\t%.9f\t%.9f\t%.9f\t%.9f\t%.9f\n'%(CD0[i],k[i],CD0cfd,kcfd,CD0cfd-CD0[i],kcfd-k[i],cl0))
fid.close()
def run_design_table():
from misc_tools import read_tabulated_data_without_header, Normalization
data = read_tabulated_data_without_header('DOE_LHS250_FFD2_3_3.txt')
pathOut = 'design_out4.txt'
ac = DesignFormulation()
ac.load_xls('Baseline1')
ac.propulsion._build_thrust_table()
ac.setup()
normalizers = list()
for l,u in zip(ac.lb, ac.ub):
normalizers.append(Normalization(l,u))
dataNew = np.zeros(data.shape)
n = data.shape[1]
for i,xNorm in enumerate(data):
dataNew[i] = np.array([normalizers[ii].denormalize(xNorm[ii]) for ii in range(n)])
ac.set_x(dataNew[i])
fid = open(pathOut,'at')
for val in ac.analysisData:
fid.write('%.20f\t'%val)
fid.write('\n')
fid.close()
print i,'\n', ac.analysisData
def _load_rbf_models(self,DOEpath=None,rsltPath=None):
if DOEpath==None:
DOEpath = r'D:\1. Current work\2014 - UAV performance code\Results\DOE\LHS_dvar9_sample24.txt'
if rsltPath==None:
rsltPath = r'D:\1. Current work\2014 - UAV performance code\Results\DOE\CFDresults.txt'
dCD0 = 0.0005
xDOE = read_tabulated_data_without_header(DOEpath)
fDOE = read_tabulated_data_without_header(rsltPath,1)
self.CLrbf = RbfMod(xDOE, fDOE[:,4]-fDOE[:,13])
self.CDrbf = RbfMod(xDOE, fDOE[:,5]-fDOE[:,14])
self.CD0rbf= RbfMod(xDOE, fDOE[:,11]-fDOE[:,19]+dCD0)
self.krbf = RbfMod(xDOE, fDOE[:,12]-fDOE[:,20])
self.SMrbf = RbfMod(xDOE, fDOE[:,10]-fDOE[:,18],0.5)
self.LDrbf = RbfMod(xDOE, fDOE[:,7] -fDOE[:,15])
self._xdoe = xDOE
def create_input_files():
from ucav_design_1 import DesignFormulation
# Longitudinal (half wing)
doePath = r'D:\1. Current work\2014 - UAV performance code\Results\norm_results.txt'
#DOE = read_tabulated_data_without_header('LHS_dvar9_sample30.txt')
DOE = read_tabulated_data_without_header(doePath)
ac = DesignFormulation()
ac.load_xls('Baseline1')
ac.setup()
startCase = 30
# Mach = ac.designGoals.cruiseMach
# altitude = ac.designGoals.cruiseAltitude
yplus = .5
wdir = 'D:\CFD'
alpha = [-2,0,2]
# beta = 2.0
niter = 5000
batFileLongitudinal = '%s\\batchCFD.bat'%wdir
fid = open(batFileLongitudinal,'at')
pathFluent = r'C:\Program Files\Ansys Inc\v130\fluent\ntbin\win64\fluent.exe'
for i,xnorm in enumerate(DOE):
if i>0:
name = '%s\\case%d'%(wdir,i+startCase)
caseName = 'case%d'%(i+startCase)
print name
ac.set_x(xnorm,False)
print ac.xCurrent
raw_input()
#FIXME: this part adds section for payload on top
#ac._adjust_root_airfoil()
ac.save_2d_figure('%s.png'%name)
igsPath = '%s.igs'%name
symCasPath = '%s_sym.cas'%name
nonsymCasPath = '%s_half.cas'%name
glfPath = '%s.glf'%name
#create_catia_wing(ac,igsPath)
create_fw_cmesh(ac,igsPath,symCasPath,nonsymCasPath,yplus,glfPath)
Sref = ac.wing.area/2.0
Cref = ac.wing.MAC
#Lref = ac.wing.span
ac._restore_root_airfoil()
CG = ac.get_cg()
#a = 2.0
# outPrefix = '%s\\results\\case%d_sym_a%d_b%d'%(wdir,i+1,a*100,beta*100)
# journalFileRel = 'case%d_sym_a%d_b%d.jou'%(i+1, a*100,beta*100)
# journalFile = '%s_sym_a%d_b%d.jou'%(name, a*100, beta*100)
#run_wing_half(symCasPath, outPrefix, ac.designGoals.fc, a, beta, Sref, Lref, CG, journalFile, niter)
for a in alpha:
outPrefix = '%s\\results\\%s_half_a%d'%(wdir,caseName,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 run_full_table_analysis(wdir):
X,lb,ub,fc = get_initial_data()
pathDOE = os.getcwd() + '\\' + wdir + '\\1. input.txt'
pathOutput = os.getcwd() + '\\' + wdir + '\\2. outputAero.txt'
clcruise = 0.4
fid = open(pathOutput,'wt')
fid.write('Au0\tAu1\tAu2\tAu3\tAu4\tAl0\tAl1\tAl2\tAl3\tAl4\tLDmax\talphaLDmax\tClmax\talphaClmax\tCdAtLDmax\tLD32max\tthickness\tcdcruise\n')
fid.close()
#designs = read_doe(pathDOE)
designs = read_tabulated_data_without_header(pathDOE)
for i,design in enumerate(designs):
design = denormalize(design,lb,ub)
af = airfoil.cst(design[0:5],design[5:10])
filename = wdir + 'polar_%d.txt'%(i+1)
result = aero_analysis(af, fc, filename)
write_output(design,result,pathOutput,clcruise)
af.write_txt(wdir + 'coordinates_%d.txt'%(i+1))
def run_optimization_1():
pathIn = "design_out4.txt"
pathInSamples = "DOE_LHS250_FFD2_3_3.txt"
learnData = read_tabulated_data_without_header(pathIn)
xNorm = read_tabulated_data_without_header(pathInSamples)
# xNorm = np.transpose(xNorm)
learnData = np.transpose(learnData)
WemptyMax = 3500.0
CnbMin = 0.0001
ClbMax = -0.05
SMmin = -0.05
SMmax = 0.10
combatRadiusMin = 1000.0
RCmin = 125.0
VmaxMin = 0.90 # Mach
LD = RbfMod(xNorm, learnData[0])
We = RbfMod(xNorm, learnData[1])
_Cnb = RbfMod(xNorm, (learnData[2]) * 1e3)
Clb = RbfMod(xNorm, learnData[3])
_SM = RbfMod(xNorm, learnData[4] * 1e3)
Rcombat = RbfMod(xNorm, learnData[5])
RC = RbfMod(xNorm, learnData[6])
Vmax = RbfMod(xNorm, learnData[7])
Cnb = lambda x: _Cnb(x) / 1e3
SM = lambda x: _SM(x) / 1e3
bnds = np.ones([9, 2])
bnds[:, 0] = -bnds[:, 0]
bnds[8, 0] = 0
bnds[7, 0] = 0
bnds = tuple(bnds)
f = lambda x: -LD(x)
g1 = lambda x: WemptyMax - We(x)
g2 = lambda x: (Cnb(x) - CnbMin) * 1e3
g3 = lambda x: ClbMax - Clb(x)
g4 = lambda x: SMmax - SM(x)
g5 = lambda x: SM(x) - SMmin
g6 = lambda x: Rcombat(x) / 1e3 - combatRadiusMin
g7 = lambda x: RC(x) - RCmin
g8 = lambda x: Vmax(x) - VmaxMin
cnstr = (
{"type": "ineq", "fun": g1},
{"type": "ineq", "fun": g2},
{"type": "ineq", "fun": g3},
{"type": "ineq", "fun": g4},
{"type": "ineq", "fun": g5},
{"type": "ineq", "fun": g6},
{"type": "ineq", "fun": g7},
{"type": "ineq", "fun": g8},
)
x0 = np.zeros(9)
rslt = minimize(f, x0, method="SLSQP", constraints=cnstr, bounds=bnds)
print rslt
rslt2 = minimize(f, x0, constraints=cnstr, bounds=bnds, options={"maxiter": 10000})
print rslt2
xopt = rslt.x
print g1(xopt), We(xopt)
print g2(xopt), Cnb(xopt)
print g3(xopt), Clb(xopt)
print g4(xopt), SM(xopt)
print g5(xopt), SM(xopt)
print g6(xopt), Rcombat(xopt)
print g7(xopt), RC(xopt)
print g8(xopt), Vmax(xopt)
ac = DesignFormulation()
ac.load_xls("Baseline1")
ac.setup()
ac.set_x(ac.x0)
x2dBaseline = ac.wing.x2d
y2dBaseline = ac.wing.y2d
print "Baseline"
print ac.analysisData
print "--->"
normalize = Normalization(ac.lb, ac.ub)
xoptDenorm = normalize.denormalize(xopt)
print xoptDenorm
ac.set_x(xoptDenorm)
x2dOptimum = ac.wing.x2d
y2dOptimum = ac.wing.y2d
print ac.analysisData, "\n---"
print (ac.analysisData[0] - LD(xopt)) / ac.analysisData[0]
print (ac.analysisData[1] - We(xopt)) / ac.analysisData[1]
print (ac.analysisData[2] - Cnb(xopt)) / ac.analysisData[2]
print (ac.analysisData[3] - Clb(xopt)) / ac.analysisData[3]
print (ac.analysisData[4] - SM(xopt)) / ac.analysisData[4]
print (ac.analysisData[5] - Rcombat(xopt)) / ac.analysisData[5]
print (ac.analysisData[6] - RC(xopt)) / ac.analysisData[6]
print (ac.analysisData[7] - Vmax(xopt)) / ac.analysisData[7]
plt.figure()
plt.hold(True)
plt.plot(x2dBaseline, y2dBaseline, "r-")
plt.plot(x2dOptimum, y2dOptimum, "k-")
plt.legend(["Baseline", "Low-fi Optimum"])
plt.show()
ac.display()
def get_parasite_drag_fw(ac,altitude=0.0):
path1 = pth.aeroCD0in
path2 = pth.aeroCD0inWave
W = ac.designGoals.grossMass*9.81
rho = ac.designGoals.fc.atm.density
V = ac.designGoals.cruiseSpeed
Sref = ac.wing.area
CL=W/(0.5*rho*V*V*Sref)
# --- friction + form drag input ---
fid1 = open(path1,'wt')
#h = ac.designGoals.cruiseAltitude
#h = convert.m_to_ft(h)
h = float(altitude)
Sref = convert.sqm_to_sqft(Sref)
Abase = 0.095
Dexit = 0.0
Ewdd = 1.8
prleak = 10.0
fid1.write('%d %.0f %.0f %.4f %.1f %.1f %.1f\n'%(1,h,Sref,Abase, Dexit, Ewdd, prleak))
ale = ac.wing.equivSweepLEdeg
aqc = ac.wing.equivSweepC4deg
ahc = ac.wing.equivSweepC2deg
a4 = ac.wing.span
a4 = convert.m_to_ft(a4)
# ---
t1 = ac.wing.airfoils[0].thickness*ac.wing.chords[0]
t2 = ac.wing.airfoils[1].thickness*ac.wing.chords[1]
Amax = (t1+t2)*ac.wing.segSpans[0]
# ---
ttc = ac.wing.equivThickness
fc = ac.wing.equivCamber
cld = CL
xa = 1.02
fid1.write('%.4f %.4f %.4f %.4f %.4f %.4f %.6f %.4f %.2f\n'%(ale,aqc,ahc,a4,Amax,ttc,fc,cld,xa))
wSwet = ac.wing.wettedArea
wSwet = convert.sqm_to_sqft(wSwet)
wRefL = convert.m_to_ft(ac.wing.MAC)
fid1.write('Wing %.4f %.4f 1 '%(wSwet,wRefL))
wtc = ac.wing.equivThickness
wc4 = ac.wing.equivSweepC4deg
wxtc = ac.wing.equivThicknessLoc
q = 1.0 #???
fid1.write('%.4f %.4f %.4f %.4f'%(wtc,wc4,wxtc,q))
fid1.close()
# --- wave drag input ---
fid2 = open(path2,'wt')
fid2.write('1 0 0 0 0 0 0 0\n')
wrle = ac.wing.equivLEradius
cam = ac.wing.equivCamber
fid2.write('%.4f %.4f %.4f %.4f %d\n'%(wtc,wxtc,wrle,cam, 1))
fid2.write('0.0394 0.5 0. 0. 0\n')
fid2.write('0. 0. 0. 0. 1\n')
fid2.write('0.04 0.5 0. 0. 0\n')
wte = ac.wing.equivSweepTEdeg
lref = convert.m_to_ft(ac.wing.MAC)
AR = ac.wing.aspectRatio
fid2.write('%.4f %.4f %.4f %.4f %.4f\n'%(ale,wte,lref,AR,Sref))
fid2.write('44.56 0. 0.29 2.24\n')
fid2.write('0. 0. 0. 0.\n')
fid2.write('44. 3. 0.277 2.48\n')
fid2.write('0. 0. 0. 0. 0.\n')
fid2.write('2\n')
fid2.write('21.08 20.92 19.364 4.97 2.9\n')
fid2.write('0.35 0.45 0.47 0.9339\n')
fid2.close()
os.system(pth.aeroCD0)
data = read_tabulated_data_without_header(pth.aeroCD0out,3)
pth.clean_drag_files()
CD = data[:-1,-1]
M = data[:-1,0]
Mdd = data[-1,0]
CDdd = data[-1,-1]
return M, CD, Mdd, CDdd
