def flap_objective(x):
af = Airfoil()
af.read_txt('GA37A315mod_reworked.txt')
flapRatio = 0.3
# lipLen = 0.13 #0.1 - 0.27
# leRad = 0.15 #0.05 - 0.25
# gap = 0.02 #0.005;0.02
# overlap = -0.02 #-0.02 0.02
defl = 35
# vratio1 = 0.73 #0.5 0.95
# vratio2 = 1.3 #1.05 1.5
# vratio3 = 0.55 #0.2 0.9
lipLen = x[0]
leRad = x[1]
gap = x[2]
overlap = x[3]
vratio1 = x[4]
vratio2 = x[5]
vratio3 = x[6]
try:
Flap = flap_geometry(af,flapRatio,lipLen, leRad, gap, overlap, defl,vratio1,vratio2,vratio3)
polar = calc_Jpolar(0.06,3e6,Flap)
clmax = ny.max(polar.cl)
#print clmax
return -clmax,[],[]
except:
return 100,[],[]
def plot_results():
# xBest =[0.18978,0.24883,0.00824,0.02996,0.50002,1.37683,0.20097]
#xBest =[0.18913399,0.13287908,0.00548619,0.02999233,0.50557791,1.49805884,0.20113115]
xBest=[0.19417077,0.24936138,0.01010853,0.0299996,0.50077753,1.39159708,0.2021984]
af = Airfoil()
af.read_txt('GA37A315mod_reworked.txt')
FlapOpt = flap_geometry(af, 0.3, xBest[0], xBest[1],xBest[2],xBest[3],35,xBest[4],xBest[5],xBest[6])
mainSec, flap, flap0 = FlapOpt
flap1 = Curves.rotate2D(flap,[0.785,-0.135],-35)
mainSec, flap, flap0 = FlapOpt
# write_txt(FlapOpt,'KLA100flap_20121213.txt')
plt.figure(1)
plt.hold(True)
plt.plot(mainSec[:,0],mainSec[:,1])
plt.plot(flap[:,0],flap[:,1])
plt.plot(flap0[:,0],flap0[:,1])
#plt.axis([0,1.1,-.5,.5])
plt.axis('equal')
plt.grid(True)
plt.show()
def test_func():
af = Airfoil()
af.read_txt('GA37A315mod_reworked.dat')
print af.up, af.coord
flapRatio = 0.3
lipLen = 0.1643088
leRad = 0.14054948
gap = 0.0157
overlap = -0.02
defl = 35
vratio1 = 0.77033947
vratio2 = 1.39164569
vratio3 = 0.55
Flap = flap_geometry(af, 0.3, lipLen, leRad,gap,overlap,35,vratio1,vratio2,vratio3)
mainSec, flap = Flap
polar = calc_Jpolar(0.06,3e6,Flap)
plt.figure(1)
plt.hold(True)
plt.plot(mainSec[:,0],mainSec[:,1])
plt.plot(flap[:,0],flap[:,1])
plt.axis([0,1.1,-.5,.5])
plt.grid(True)
plt.show()
def create_propeller(x,afOld):
diameter = 1.75
hubDiameter = 0.3
hubX = hubDiameter / diameter
baseAfPath = 'clark-Y.txt'
chordX = array([hubX,0.35,0.5,0.75,0.95])
pitchX = array([hubX,0.35,0.5,0.75,0.95])
thickX = array([hubX,0.35,0.5,0.75,0.95])
xnew = linspace(hubX,0.95,10)
betaSet = pitchX[3]
n1,n2,n3 = len(chordX), len(pitchX), len(thickX)
chordY = x[0:n1]
pitchY = x[n1:n1+n2]
thickY = x[n1+n2:]
method = 'spline'
chord = _interpolate(chordX,chordY,xnew,method)
pitch = _interpolate(pitchX,pitchY,xnew,method)
thick = _interpolate(thickX,thickY,xnew,method)
prop = propeller()
if afOld==None:
af = list()
for tc in thick:
afnew = Airfoil()
afnew.read_txt(baseAfPath)
afnew.analyze_geometry()
afnew.scale_thickness(tc,False)
afnew.build_aero_table(alphaSeq=[-40.0,40.0,1.0])
af.append(afnew)
prop.airfoil = af
else:
prop.airfoil = afOld
prop.name = 'MDO_project'
prop.diameter = diameter
prop.hubDiameter = hubDiameter
prop.chord = chord
prop.beta = pitch
prop.x = xnew
prop.r = xnew*diameter/2.0
prop.radius = diameter/2.0
prop.numBlades = 3.0
prop.thickness = thick
prop.numStations = len(xnew)
prop.analyze_geometry()
prop.set_beta(betaSet)
# if show:
# fig = plt.figure(1)
# ax1 = fig.add_subplot(311)
# ax1.grid(True)
# ax1.hold(True)
# ax1.plot(xnew,chord)
# ax2 = fig.add_subplot(312)
# ax2.grid(True)
# ax2.plot(xnew,pitch)
# ax3 = fig.add_subplot(313)
# ax3.grid(True)
# ax3.plot(xnew,thick)
# plt.show()
return prop
def flap_geometry2(x=None,args=1):
if x==None:
x = ny.array([0.15, 0.3, 0.05, 0.5, 0.1, 0.5, 0.02, 0.02])
flapRatio = 0.7
defl = 35.0
airfoil = Airfoil()
airfoil.read_txt('aiaa_cfd_final_optimum.txt')
offset = 0.005 # main section flap offset
lipTe = 0.0033 # trailing edge thickness
rTe = 0.01 # trailing edge radius
exitLipLen = x[0]
leRadPos = x[1]
entryLipLen = x[2]
v1 = x[3]
v2 = x[4]
v3 = x[5]
gap = x[6]
overlap = x[7]
upNode = ny.zeros([4,2])
loNode = ny.zeros([4,2])
upCurve = Curves.xyCurve(airfoil.upPts)
loCurve = Curves.xyCurve(airfoil.loPts)
thickness = upCurve(flapRatio)-loCurve(flapRatio) #local thickness
leRad = v2 * thickness # V2 length
leRadPos = leRadPos * thickness + loCurve(flapRatio)
upNode[0,0] = flapRatio + exitLipLen
upNode[0,1] = upCurve(upNode[0,0])
tan0 = upCurve.tan(upNode[0,0])
upNode[1,0] = upNode[0,0] - exitLipLen*v1
upNode[1,1] = -(upNode[0,0]-upNode[1,0])*tan0 + upNode[0,1]
loNode[0,0] = flapRatio + entryLipLen
loNode[0,1] = loCurve(loNode[0,0])
tan1 = loCurve.tan(loNode[0,0])
loNode[1,0] = loNode[0,0] - entryLipLen*v3
loNode[1,1] = loNode[0,1] - (loNode[0,0]-loNode[1,0])*tan1
upNode[2,0] = flapRatio
loNode[2,0] = flapRatio
upNode[3,0] = flapRatio
loNode[3,0] = flapRatio
upNode[3,1] = leRadPos
loNode[3,1] = leRadPos
upNode[2,1] = upNode[3,1] + leRad
loNode[2,1] = loNode[3,1] - leRad
curve3 = Curves.BezierCurve(upNode,10)
curve4 = Curves.BezierCurve(loNode,10)
curve4e = ny.flipud(curve4)
curve4e[:,2] = curve4[:,2]
curve4e = curve4e[1:]
curve4e[:,2] = curve4e[:,2]+1.0
curve11 = ny.vstack([curve3,curve4e])
curve11offset = Curves.xytCurveOffset(curve11,-offset)
curve6 = Curves.xyCurveSplit(upCurve.pts,upNode[0,0])
curve7 = Curves.xyCurveSplit(loCurve.pts,0,loNode[0,0])
curve8 = Curves.xyCurveSplit(loCurve.pts,loNode[0,0])
curve9, curve10 = Curves.trimTe(airfoil.upPts,curve11offset,lipTe)
curve7, curve10 = Curves.splitCurveSimple(curve7,curve10,[0,0])
curve12, circle1, curve13 = Curves.roundCorner(curve7,curve10,rTe)
mainSec = ny.vstack([ny.flipud(curve9),curve12,circle1,ny.flipud(curve13[:,0:2])])
flapSec1 = ny.vstack([ny.flipud(curve6)[:-1,:],curve11[:-1,0:2],curve8])
#flapSec0 = flapSec1
flapSec1 = Curves.rotate2D(flapSec1,[0.7,-.1],defl)
flapAdd = Curves.rotate2D(curve11,[0.7,-.1],defl)
refPt = mainSec[-1]
moveX1 = ny.min(flapSec1[:,0]) - refPt[0] + overlap
flapSec1[:,0] = flapSec1[:,0] - moveX1
flapAdd[:,0] = flapAdd[:,0] - moveX1
#gap
dy = Curves.adjustGap(flapAdd,refPt,gap)
flapSec1[:,1] = flapSec1[:,1] + dy
return mainSec, flapSec1