def costFcn(X):
airfoilPath = 'GA37A315mod.dat'
nodes1 = ny.zeros([3,2])
nodes2 = ny.zeros([3,2])
vectLen1 = ny.zeros([3])
nodes1[0,0] = X[0]
nodes1[1,1] = X[1]
nodes1[2,0] = X[2]
nodes2[0,0] = X[3]
vectLen1[0] = X[4]
vectLen1[1] = X[5]
vectLen1[2] = X[6]
theta = X[7]
overlap = X[8]
gap = X[9]
teThickness = 0.002
deflection = 35
nodes1[1,0] = 0.7 #flap chord ratio
Mach = 0.16
Re = 4e6
alphaStart = -20
alphaEnd = 20
alphaStep = 1
try:
airfoil = flapGeom.getFlap(airfoilPath, nodes1,nodes2, vectLen1, theta, gap, overlap, deflection,teThickness)
polar = afAnalysis.polar(airfoil)
polar.calcJpolar(Mach,Re,alphaStart,alphaEnd,alphaStep,True)
f = -polar.CLmax
g = 10. - polar.ClmaxAlpha
except: f,g = 100,1
h = []
return f,g,h
def costFcn(X):
airfoilPath = 'FinalOptimum20120720.dat'
node1 = ny.zeros([3,2])
node2 = ny.zeros([3,2])
vectLenRatio1 = ny.zeros([3])
node1[0,0] = X[0]
node1[1,1] = X[1]
node1[2,0] = X[2]
node2[0,0] = X[3]
vectLenRatio1[0] = X[4]
vectLenRatio1[1] = X[5]
vectLenRatio1[2] = X[6]
theta = X[7]
overlap = X[8]
gap = X[9]
zTE = 0.002
deflection = 35
node1[1,0] = 0.7 #flap chord ratio
Mach = 0.0955
Re = 2285283
alphaStart = -10
alphaEnd = 15
alphaStep = 1
try:
airfoil = flapGeom2.getFlap(airfoilPath, node1,node2, vectLenRatio1, theta, gap, overlap, deflection,zTE)
polar = afAnalysis.polar(airfoil)
polar.calcJpolar(Mach,Re,alphaStart,alphaEnd,alphaStep,True)
f = -polar.CLmax
#g = 5. - polar.ClmaxAlpha
except: f = 100
h = []
g = []
return f,g,h
def CostFcn(X):
Au = X[0:3]
Al = X[4:6]
Al = ny.hstack([-Au[0],Al])
Mach = 0.16
Re = 4.17e6
alphaStart = -10
alphaEnd = 20
alphaStep = 1.0
clreq = 0.2
af = CST.CSTairfoil(Au,Al,ny.array([0.5,1.0]),80)
tc = ny.max(af.up[:,1]-af.lo[:,1])
g = ny.zeros([4])
polar = afAnalysis.polar(af)
polar.calcXpolar(Mach,Re,alphaStart,alphaEnd,alphaStep,50,False)
g[0] = 0.13 - tc
g[1] = tc - 0.18
g[2] = 1.6 - polar.CLmax
f,alpha = polar.cdAtcl(clreq)
g[3] = -alpha
h = []
return f, g,h
def costFcn(X,deflection):
airfoilPath = 'GA37A315mod.dat'
node1 = ny.zeros([3,2])
node2 = ny.zeros([3,2])
vectLenRatio1 = ny.zeros([3])
node1[0,0] = X[0]
node1[1,1] = X[1]
node1[2,0] = X[2]
node2[0,0] = X[3]
vectLenRatio1[0] = X[4]
vectLenRatio1[1] = X[5]
vectLenRatio1[2] = X[6]
theta = X[7]
overlap = X[8]
gap = X[9]
zTE = 0.002
#deflection = 35
node1[1,0] = 0.7 #flap chord ratio
Mach = 0.16
Re = 4e6
alphaStart = -20
alphaEnd = 10
alphaStep = 1
try:
airfoil = flapGeom2.getFlap(airfoilPath, node1,node2, vectLenRatio1, theta, gap, overlap, deflection,zTE)
polar = afAnalysis.polar(airfoil)
#polar.calcJpolar(Mach,Re,alphaStart,alphaEnd,alphaStep,True)
#f = -polar.CLmax
#g = 5. - polar.ClmaxAlpha
except: f = 100
f = []
h = []
g = []
wdir = r'D:\Documents\My Documents\1. Classes\5 Sem - Human Computer Interaction for MDO\term project\DoE'
filename1 = ('flap overlap%.2f gap%.2f defl%.2f.txt'%(100*X[8],100*X[9],deflection))
filename2 = ('flap overlap%.2f gap%.2f defl%.2f.iges'%(100*X[8],100*X[9],deflection))
filepath1 = wdir + '\\' + filename1
filepath2 = wdir + '\\' + filename2
afLib.writeFlap(filepath1,airfoil)
polar.saveAsIgs(filepath2,airfoil,True)
plt.figure(1)
plt.axis([0,1.2,-.5,.5])
plt.grid(True)
plt.hold(True)
plt.plot(airfoil.mainSec[:,0],airfoil.mainSec[:,1])
plt.plot(airfoil.flap[:,0],airfoil.flap[:,1])
plt.show()
return f,g,h
def final_result(X):
airfoilPath = 'FinalOptimum20120720.dat'
node1 = ny.zeros([3,2])
node2 = ny.zeros([3,2])
vectLenRatio1 = ny.zeros([3])
node1[0,0] = X[0]
node1[1,1] = X[1]
node1[2,0] = X[2]
node2[0,0] = X[3]
vectLenRatio1[0] = X[4]
vectLenRatio1[1] = X[5]
vectLenRatio1[2] = X[6]
theta = X[7]
overlap = X[8]
gap = X[9]
zTE = 0.002
deflection = 35
node1[1,0] = 0.7 #flap chord ratio
Mach = 0.0955
Re = 2285283
alphaStart = -10
alphaEnd = 15
alphaStep = 1
airfoil = flapGeom2.getFlap(airfoilPath, node1,node2, vectLenRatio1, theta, gap, overlap, deflection,zTE)
polar = afAnalysis.polar(airfoil)
polar.calcJpolar(Mach,Re,alphaStart,alphaEnd,alphaStep,True)
print polar.CLmax
afAnalysis.afLib.writeFlap('optimized flap.dat', airfoil)
plt.figure(2)
plt.plot(airfoil.mainSec[:,0],airfoil.mainSec[:,1])
plt.hold(True)
plt.grid(True)
plt.plot(airfoil.flap[:,0],airfoil.flap[:,1])
plt.axis([0,1.2,-.5,.5])
plt.show()
