def NACA4Blade(name,camber_root,camber_tip,camber_position,\
thickness,bladeHeight,twistAngle,rootChord,tipChord,\
centerOfTwist,nspan,npts):
#//////////////////////
#//Inputs:
#// camber_max: %chord
#// camber_position: location of max camber %chord
#// thickness: max thickness of airfoil as %chord
#// bladeHeight: height of blade
#// twist: degrees/unit height
#// centerOfTwist: %chord
#// nspan: number of span wise subdivisions
#// npts: number of pts used to discretise both the upper and lower airfoil profile surface.
#Twist per unit length
twist=math.radians(twistAngle)/bladeHeight
mr=camber_root/100
mt=camber_tip/100
p=camber_position/100
t=thickness/100
centerOfTwist[0]= centerOfTwist[0]/100
centerOfTwist[1]/=100
x=[]
yt=[]
yc=[]
xu=[]
yu=[]
xl=[]
yl=[]
xuTwist=[0]*npts
yuTwist=[0]*npts
xlTwist=[0]*npts
ylTwist=[0]*npts
verts=[]
faces=[]
origin=(0,0,0)
#Generate vertex coordinates with twist and scale along the span
dspan = bladeHeight/nspan
for j in range(0,nspan+1):
### bad use of memory, Fix it. Does this matter in Python?
x=[]
yt=[]
yc=[]
xu=[]
xl=[]
yu=[]
yl=[]
m=(1-j/(nspan))*mr + j/nspan*mt
#Generate vertex coordinates for unmodified airfoil shape
for i in range(0,npts+1):
x.append(1-math.cos(i*(math.pi/2)/npts))
yt.append(t/0.2*(0.2969*math.pow(x[i],0.5)-0.126*x[i]-0.3516*math.pow(x[i],2)+0.2843*math.pow(x[i],3) - 0.1015*math.pow(x[i],4)))
if(x[i]<p):
yc.append(m/pow(p,2)*(2*p*x[i] - pow(x[i],2)))
dycdx = 2*m/pow(p,2)*(p-x[i])
else:
yc.append(m/pow(1-p,2)*(1 - 2*p + 2*p*x[i] - pow(x[i],2)))
dycdx = 2*m/pow(1-p,2)*(p-x[i])
#Shift foil to center of twist
x[i] -= centerOfTwist[0]
yc[i] -= centerOfTwist[1]
xu.append(x[i] - yt[i]*(math.sin(math.atan(dycdx))))
yu.append(yc[i] + yt[i]*(math.cos(math.atan(dycdx))))
xl.append(x[i] + yt[i]*(math.sin(math.atan(dycdx))))
yl.append(yc[i] - yt[i]*(math.cos(math.atan(dycdx))))
#####
angle = twist*j*dspan
chord = rootChord - j*dspan*(rootChord-tipChord)/bladeHeight
for i in range(0,npts):
xuTwist[i] = xu[i]*math.cos(angle) -yu[i]*math.sin(angle)
yuTwist[i] = xu[i]*math.sin(angle) +yu[i]*math.cos(angle)
xuTwist[i] *= chord
yuTwist[i] *= chord
verts.append((xuTwist[i],yuTwist[i],j*dspan))
for i in range(0,npts):
xlTwist[i] = xl[i]*math.cos(angle) -yl[i]*math.sin(angle)
ylTwist[i] = xl[i]*math.sin(angle) +yl[i]*math.cos(angle)
xlTwist[i] *= chord
ylTwist[i] *= chord
verts.append((xlTwist[i],ylTwist[i],j*dspan))
#Generate Polies from vertex IDs
#Bottom Cap
faces.append((0,1,npts+1))
for i in range(0,npts-1):
faces.append((i,i+1,npts+i+1))
faces.append((i,npts+i+1,npts+i))
#Middle
nPerStage = npts*2
for j in range(0,nspan):
for i in range(0,npts-1):
faces.append((nPerStage*j+i,nPerStage*(j+1)+i,nPerStage*(j+1)+i+1))
faces.append((nPerStage*j+i,nPerStage*(j+1)+i+1,nPerStage*j+i+1))
for i in range(0,npts-1):
faces.append((nPerStage*j+i+npts,nPerStage*(j+1)+i+1+npts,nPerStage*(j+1)+i+npts))
faces.append((nPerStage*j+i+npts,nPerStage*j+i+1+npts,nPerStage*(j+1)+i+1+npts))
faces.append((nPerStage*j+npts-1,nPerStage*(j+1)+npts-1,nPerStage*(j+1)+npts*2-1))
faces.append((nPerStage*j+npts-1,nPerStage*(j+1)+npts*2-1,nPerStage*(j)+npts*2-1))
#Top Cap
faces.append((nPerStage*(nspan),nPerStage*(nspan)+1,nPerStage*(nspan)+npts+1))
for i in range(0,npts-1):
faces.append((nPerStage*(nspan)+i,nPerStage*(nspan)+npts+i+1,nPerStage*(nspan)+i+1))
faces.append((nPerStage*(nspan)+i,nPerStage*(nspan)+npts+i,nPerStage*(nspan)+npts+i+1))
#Create Object
ob1 = DLUtils.createMesh(name, origin, verts, [], faces)
#reset Vars
centerOfTwist[0]*=100
centerOfTwist[1]*=100
def Propeller(propName,propDia,pitch,\
hubHeight,hubDia,axleDia,\
PropellerProps,\
bladeTransition,nspan,npts,nBlades):
p = PropellerProps
res = 64 #used to define cylinder resolution.
#initialising arrays we'll need.
verts = []
tmpVerts = []
tmpVert = [0, 0, 0]
faces = []
origin = (0, 0, 0)
centerOfTwist = [0, 0]
p.rootSlope *= math.pi / 180
p.transitionSlope *= math.pi / 180
p.tipSlope *= math.pi / 180
p.rootSkewSlope *= math.pi / 180
p.transitionSkewSlope *= math.pi / 180
p.tipSkewSlope *= math.pi / 180
#An array of the chord lengths at each span point
chordArray = []
#An array of the NACA4 digits at each span point.
NACAArray = []
#An array that holds the position along the blade span of the airfoil cross-sections
sPos = []
#An array that holds the amount of skew of each airfoil cross-section
skew = []
#Blade root will be at center of rotation.
bladeHeight = propDia / 2
bladeLen = bladeHeight - bladeTransition
dSpan = bladeHeight / nspan
lastI = 0
for i in range(0, nspan + 1):
span = i * dSpan
if (span < bladeTransition):
#Using cubic spline interpolation.
t = span / bladeTransition
tm1 = 1 - t
#root to transition point interpolation
y1 = p.rootChord
y2 = p.rootChord + math.sin(p.rootSlope) * p.rootStrength
y3 = p.transitionChord - math.sin(
p.transitionSlope) * p.transitionStrengthRoot
y4 = p.transitionChord
chord = pow(tm1, 3) * y1 + 3 * pow(
tm1, 2) * t * y2 + 3 * tm1 * pow(t, 2) * y3 + pow(t, 3) * y4
chordArray.append(chord)
x1 = 0
x2 = math.cos(p.rootSlope) * p.rootStrength
x3 = (bladeTransition -
math.cos(p.transitionSlope) * p.transitionStrengthRoot)
x4 = bladeTransition
x = pow(tm1, 3) * x1 + 3 * pow(tm1, 2) * t * x2 + 3 * tm1 * pow(
t, 2) * x3 + pow(t, 3) * x4
sPos.append(x)
y1 = p.rootThick
y2 = p.rootThick + math.sin(p.rootThickSlope) * p.rootThickStrength
y3 = p.transitionThick - math.sin(
p.transitionThickSlope) * p.transitionThickStrengthRoot
y4 = p.transitionThick
thickPt = pow(tm1, 3) * y1 + 3 * pow(
tm1, 2) * t * y2 + 3 * tm1 * pow(t, 2) * y3 + pow(t, 3) * y4
print(thickPt)
NACAArray.append([
5, 3,
int(thickPt * 10),
int(thickPt * 100 - int(thickPt * 10) * 10)
])
y1 = p.rootSkew
y2 = p.rootSkew + math.sin(p.rootSkewSlope) * p.rootSkewStrength
y3 = p.transitionSkew - math.sin(
p.transitionSkewSlope) * p.transitionSkewStrengthRoot
y4 = p.transitionSkew
skewPt = pow(tm1, 3) * y1 + 3 * pow(
tm1, 2) * t * y2 + 3 * tm1 * pow(t, 2) * y3 + pow(t, 3) * y4
skew.append(skewPt)
else:
#Using cubic spline interpolation.
t = (span - bladeTransition) / bladeLen
tm1 = 1 - t
y1 = p.transitionChord
y2 = p.transitionChord + math.sin(
p.transitionSlope) * p.transitionStrengthTip
y3 = p.tipChord - math.sin(p.tipSlope) * p.tipStrength
y4 = p.tipChord
chord = pow(tm1, 3) * y1 + 3 * pow(
tm1, 2) * t * y2 + 3 * tm1 * pow(t, 2) * y3 + pow(t, 3) * y4
chordArray.append(chord)
x1 = 0
x2 = math.cos(p.transitionSlope) * p.transitionStrengthTip
x3 = (bladeLen - math.cos(p.tipSlope) * p.tipStrength)
x4 = bladeLen
x = pow(tm1, 3) * x1 + 3 * pow(tm1, 2) * t * x2 + 3 * tm1 * pow(
t, 2) * x3 + pow(t, 3) * x4
sPos.append(bladeTransition + x)
y1 = p.transitionThick
y2 = p.transitionThick + math.sin(
p.rootThickSlope) * p.rootThickStrength
y3 = p.tipThick - math.sin(
p.transitionThickSlope) * p.transitionThickStrengthTip
y4 = p.tipThick
thickPt = pow(tm1, 3) * y1 + 3 * pow(
tm1, 2) * t * y2 + 3 * tm1 * pow(t, 2) * y3 + pow(t, 3) * y4
NACAArray.append([
5, 3,
int(thickPt * 10),
int(thickPt * 100 - int(thickPt * 10) * 10)
])
y1 = p.transitionSkew
y2 = p.transitionSkew + math.sin(
p.transitionSkewSlope) * p.transitionSkewStrengthTip
y3 = p.tipSkew - math.sin(p.tipSkewSlope) * p.tipSkewStrength
y4 = p.tipSkew
skewPt = pow(tm1, 3) * y1 + 3 * pow(
tm1, 2) * t * y2 + 3 * tm1 * pow(t, 2) * y3 + pow(t, 3) * y4
skew.append(skewPt)
#error check of inputs
if (len(chordArray) != nspan or len(NACAArray) != nspan):
print(
"The size of the array of chord lengths or the array of airfoil NACA digits does not match the number of span points used to define the blade geometry."
)
#Delete any existing prop geoms
DLUtils.DeleteMesh(propName)
#Generate Hub
DLUtils.DrawCylinder("Hub", hubDia, 0, hubHeight,
res) #use a 0.001m tolerance which we'll trim off.
cyl = bpy.data.objects["Hub"]
cyl.name = propName
cyl.data.name = propName
DLUtils.SelectOnly(propName)
bpy.ops.transform.rotate(value=math.radians(90), axis=(0.0, 1.0, 0.0))
DLUtils.MoveObject(propName, [2.0, 0, 0])
areaArray = []
#Generate vertex coordinates with twist and scale along the span
for i in range(0, nspan + 1):
span = sPos[i] #i*dSpan
if (span == 0):
twistAngle = 0
elif (span < bladeTransition):
twistAngle = math.atan(
pitch / (2 * math.pi * span)) * span / bladeTransition
else:
twistAngle = math.atan(pitch / (2 * math.pi * span))
#get the airfoil profile vertices
tmpVerts = TurboMachLib.NACA4Profile(camber=NACAArray[i][0],
thickness=NACAArray[i][2] * 10 +
NACAArray[i][3],
camberPos=NACAArray[i][1] * 10,
chord=chordArray[i],
npts=npts)
areaArray.append(0)
centerOfTwist[0] = chordArray[i] * skew[i]
#centerOfTwist[1] = raiseFoil
for v in range(0, len(tmpVerts)):
#shift all verts for twisting
tmpVerts[v][0] -= centerOfTwist[0]
tmpVerts[v][1] -= centerOfTwist[1]
#Twist the airfoil vertices. First we shift them to get the desired center of rotation.
tmpVert[0] = tmpVerts[v][0] * math.cos(
twistAngle) - tmpVerts[v][1] * math.sin(twistAngle)
tmpVert[1] = tmpVerts[v][0] * math.sin(
twistAngle) + tmpVerts[v][1] * math.cos(twistAngle)
#shift all verts to their proper span location in Z
tmpVert[
2] = span + 0.01 * bladeHeight #Shift blade by 1% of blade height to prevent poor boolean ops
#append the vert to the master vertex list
verts.append((tmpVert[0], tmpVert[1], tmpVert[2]))
if (v != 0):
dx = abs(verts[len(verts) - 1][0] - verts[len(verts) - 2][0])
dy = abs(verts[len(verts) - 1][1] +
verts[len(verts) - 2][1]) / 2
areaArray[i] += dy * dx
#Generate Polies from vertex IDs
#Bottom Cap
faces.append((0, 1, npts))
for i in range(1, npts - 1):
faces.append((i, i + 1, npts + i))
faces.append((i, npts + i, npts + i - 1))
#Middle
nPerStage = npts * 2 - 1
for j in range(0, nspan):
#Top Side
for i in range(0, npts - 1):
faces.append((nPerStage * j + i, nPerStage * (j + 1) + i,
nPerStage * (j + 1) + i + 1))
faces.append((nPerStage * j + i, nPerStage * (j + 1) + i + 1,
nPerStage * j + i + 1))
#First strip for bottom side (hooks to verts from top side)
faces.append(
(nPerStage * j, nPerStage * (j + 1) + npts, nPerStage * (j + 1)))
faces.append(
(nPerStage * j, nPerStage * j + npts, nPerStage * (j + 1) + npts))
#Rest of bottom side
for i in range(0, npts - 2):
faces.append(
(nPerStage * j + i + npts, nPerStage * (j + 1) + i + npts + 1,
nPerStage * (j + 1) + i + npts))
faces.append(
(nPerStage * j + i + npts, nPerStage * j + i + npts + 1,
nPerStage * (j + 1) + i + npts + 1))
#Back face
faces.append((nPerStage * j + npts - 1, nPerStage * (j + 1) + npts - 1,
nPerStage * (j + 1) + npts * 2 - 2))
faces.append(
(nPerStage * j + npts - 1, nPerStage * (j + 1) + npts * 2 - 2,
nPerStage * (j) + npts * 2 - 2))
#Top Cap
faces.append((nPerStage * (nspan), nPerStage * (nspan) + 1,
nPerStage * (nspan) + npts))
for i in range(1, npts - 1):
faces.append((nPerStage * (nspan) + i, nPerStage * (nspan) + npts + i,
nPerStage * (nspan) + i + 1))
faces.append(
(nPerStage * (nspan) + i, nPerStage * (nspan) + npts + i - 1,
nPerStage * (nspan) + npts + i))
#Create Blender object for the blade
dAngle = 360.0 / nBlades
for i in range(0, nBlades):
print("Draw Blade_" + str(i))
blade = DLUtils.createMesh("Blade_" + str(i), origin, verts, [], faces)
DLUtils.SelectOnly("Blade_" + str(i))
bpy.ops.transform.rotate(value=math.radians(90), axis=(0.0, 0.0, 1.0))
bpy.ops.transform.rotate(value=math.radians(dAngle) * i,
axis=(1.0, 0.0, 0.0))
#Union the blades to the hub
for i in range(0, nBlades):
print("Union: Blade_" + str(i))
DLUtils.BooleanMesh(propName, "Blade_" + str(i), "UNION", True)
#trim the blades to hub height
DLUtils.DrawBox("box", hubDia * 1.1, hubDia * 1.1, hubDia * 1.1)
DLUtils.MoveObject("box", [propDia / 2 + hubHeight / 2 + 0.001, 0, 0])
DLUtils.BooleanMesh(propName, "box", "DIFFERENCE", True)
#cut the axle hole
DLUtils.DrawCylinder("hole", axleDia, 0, hubHeight * 2, res)
DLUtils.SelectOnly("hole")
bpy.ops.transform.rotate(value=math.radians(90), axis=(0.0, 1.0, 0.0))
DLUtils.BooleanMesh(propName, "hole", 'DIFFERENCE', True)
#Cut room for the axle shive
DLUtils.DrawCylinder("ShiveHole", (hubDia - axleDia) / 4 + axleDia, 0,
hubHeight / 1.5, res)
DLUtils.SelectOnly("ShiveHole")
bpy.ops.transform.rotate(value=math.radians(90), axis=(0.0, 1.0, 0.0))
DLUtils.BooleanMesh(propName, "ShiveHole", 'DIFFERENCE', True)
#DLUtils.MoveObject(propName,[2.0,0,0])
#trim the blades to the proper dia
DLUtils.DrawCylinder("BladeTrim", propDia, 0, propDia, 256)
DLUtils.SelectOnly("BladeTrim")
bpy.ops.transform.rotate(value=math.radians(90), axis=(0.0, 1.0, 0.0))
DLUtils.BooleanMesh(propName, "BladeTrim", 'INTERSECT', True)
#done!
print((BladeAxialStress(sPos, areaArray, 40e6, 1300, 15000)))
return
def NACA4Blade(name,camber_root,camber_tip,camber_position,\
thickness,bladeHeight,twistAngle,rootChord,tipChord,\
centerOfTwist,nspan,npts):
#//////////////////////
#//Inputs:
#// camber_max: %chord
#// camber_position: location of max camber %chord
#// thickness: max thickness of airfoil as %chord
#// bladeHeight: height of blade
#// twist: degrees/unit height
#// centerOfTwist: %chord
#// nspan: number of span wise subdivisions
#// npts: number of pts used to discretise both the upper and lower airfoil profile surface.
#Twist per unit length
twist = math.radians(twistAngle) / bladeHeight
mr = camber_root / 100
mt = camber_tip / 100
p = camber_position / 100
t = thickness / 100
centerOfTwist[0] = centerOfTwist[0] / 100
centerOfTwist[1] /= 100
x = []
yt = []
yc = []
xu = []
yu = []
xl = []
yl = []
xuTwist = [0] * npts
yuTwist = [0] * npts
xlTwist = [0] * npts
ylTwist = [0] * npts
verts = []
faces = []
origin = (0, 0, 0)
#Generate vertex coordinates with twist and scale along the span
dspan = bladeHeight / nspan
for j in range(0, nspan + 1):
### bad use of memory, Fix it. Does this matter in Python?
x = []
yt = []
yc = []
xu = []
xl = []
yu = []
yl = []
m = (1 - j / (nspan)) * mr + j / nspan * mt
#Generate vertex coordinates for unmodified airfoil shape
for i in range(0, npts + 1):
x.append(1 - math.cos(i * (math.pi / 2) / npts))
yt.append(
t / 0.2 *
(0.2969 * math.pow(x[i], 0.5) - 0.126 * x[i] -
0.3516 * math.pow(x[i], 2) + 0.2843 * math.pow(x[i], 3) -
0.1015 * math.pow(x[i], 4)))
if (x[i] < p):
yc.append(m / pow(p, 2) * (2 * p * x[i] - pow(x[i], 2)))
dycdx = 2 * m / pow(p, 2) * (p - x[i])
else:
yc.append(m / pow(1 - p, 2) *
(1 - 2 * p + 2 * p * x[i] - pow(x[i], 2)))
dycdx = 2 * m / pow(1 - p, 2) * (p - x[i])
#Shift foil to center of twist
x[i] -= centerOfTwist[0]
yc[i] -= centerOfTwist[1]
xu.append(x[i] - yt[i] * (math.sin(math.atan(dycdx))))
yu.append(yc[i] + yt[i] * (math.cos(math.atan(dycdx))))
xl.append(x[i] + yt[i] * (math.sin(math.atan(dycdx))))
yl.append(yc[i] - yt[i] * (math.cos(math.atan(dycdx))))
#####
angle = twist * j * dspan
chord = rootChord - j * dspan * (rootChord - tipChord) / bladeHeight
for i in range(0, npts):
xuTwist[i] = xu[i] * math.cos(angle) - yu[i] * math.sin(angle)
yuTwist[i] = xu[i] * math.sin(angle) + yu[i] * math.cos(angle)
xuTwist[i] *= chord
yuTwist[i] *= chord
verts.append((xuTwist[i], yuTwist[i], j * dspan))
for i in range(0, npts):
xlTwist[i] = xl[i] * math.cos(angle) - yl[i] * math.sin(angle)
ylTwist[i] = xl[i] * math.sin(angle) + yl[i] * math.cos(angle)
xlTwist[i] *= chord
ylTwist[i] *= chord
verts.append((xlTwist[i], ylTwist[i], j * dspan))
#Generate Polies from vertex IDs
#Bottom Cap
faces.append((0, 1, npts + 1))
for i in range(0, npts - 1):
faces.append((i, i + 1, npts + i + 1))
faces.append((i, npts + i + 1, npts + i))
#Middle
nPerStage = npts * 2
for j in range(0, nspan):
for i in range(0, npts - 1):
faces.append((nPerStage * j + i, nPerStage * (j + 1) + i,
nPerStage * (j + 1) + i + 1))
faces.append((nPerStage * j + i, nPerStage * (j + 1) + i + 1,
nPerStage * j + i + 1))
for i in range(0, npts - 1):
faces.append(
(nPerStage * j + i + npts, nPerStage * (j + 1) + i + 1 + npts,
nPerStage * (j + 1) + i + npts))
faces.append(
(nPerStage * j + i + npts, nPerStage * j + i + 1 + npts,
nPerStage * (j + 1) + i + 1 + npts))
faces.append((nPerStage * j + npts - 1, nPerStage * (j + 1) + npts - 1,
nPerStage * (j + 1) + npts * 2 - 1))
faces.append(
(nPerStage * j + npts - 1, nPerStage * (j + 1) + npts * 2 - 1,
nPerStage * (j) + npts * 2 - 1))
#Top Cap
faces.append((nPerStage * (nspan), nPerStage * (nspan) + 1,
nPerStage * (nspan) + npts + 1))
for i in range(0, npts - 1):
faces.append(
(nPerStage * (nspan) + i, nPerStage * (nspan) + npts + i + 1,
nPerStage * (nspan) + i + 1))
faces.append((nPerStage * (nspan) + i, nPerStage * (nspan) + npts + i,
nPerStage * (nspan) + npts + i + 1))
#Create Object
ob1 = DLUtils.createMesh(name, origin, verts, [], faces)
#reset Vars
centerOfTwist[0] *= 100
centerOfTwist[1] *= 100
def Propeller(propName,propDia,pitch,\
hubHeight,hubDia,axleDia,\
PropellerProps,\
bladeTransition,nspan,npts,nBlades):
p=PropellerProps
res = 64 #used to define cylinder resolution.
#initialising arrays we'll need.
verts = []
tmpVerts = []
tmpVert = [0,0,0]
faces = []
origin=(0,0,0)
centerOfTwist = [0,0]
p.rootSlope *= math.pi/180
p.transitionSlope *= math.pi/180
p.tipSlope *= math.pi/180
p.rootSkewSlope *= math.pi/180
p.transitionSkewSlope *= math.pi/180
p.tipSkewSlope *= math.pi/180
#An array of the chord lengths at each span point
chordArray = []
#An array of the NACA4 digits at each span point.
NACAArray = []
#An array that holds the position along the blade span of the airfoil cross-sections
sPos = []
#An array that holds the amount of skew of each airfoil cross-section
skew = []
#Blade root will be at center of rotation.
bladeHeight = propDia/2
bladeLen = bladeHeight - bladeTransition
dSpan = bladeHeight/nspan
lastI = 0;
for i in range(0,nspan+1):
span = i*dSpan
if(span < bladeTransition):
#Using cubic spline interpolation.
t = span/bladeTransition
tm1 = 1-t
#root to transition point interpolation
y1 = p.rootChord
y2 = p.rootChord + math.sin(p.rootSlope)*p.rootStrength
y3 = p.transitionChord - math.sin(p.transitionSlope)*p.transitionStrengthRoot
y4 = p.transitionChord
chord = pow(tm1,3)*y1 + 3*pow(tm1,2)*t*y2 + 3*tm1*pow(t,2)*y3 + pow(t,3)*y4
chordArray.append(chord)
x1=0
x2=math.cos(p.rootSlope)*p.rootStrength
x3=(bladeTransition-math.cos(p.transitionSlope)*p.transitionStrengthRoot)
x4=bladeTransition
x = pow(tm1,3)*x1 + 3*pow(tm1,2)*t*x2 + 3*tm1*pow(t,2)*x3 + pow(t,3)*x4
sPos.append(x)
y1 = p.rootThick
y2 = p.rootThick + math.sin(p.rootThickSlope)*p.rootThickStrength
y3 = p.transitionThick - math.sin(p.transitionThickSlope)*p.transitionThickStrengthRoot
y4 = p.transitionThick
thickPt = pow(tm1,3)*y1 + 3*pow(tm1,2)*t*y2 + 3*tm1*pow(t,2)*y3 + pow(t,3)*y4
print(thickPt)
NACAArray.append([5,3,int(thickPt*10),int(thickPt*100-int(thickPt*10)*10)])
y1 = p.rootSkew
y2 = p.rootSkew + math.sin(p.rootSkewSlope)*p.rootSkewStrength
y3 = p.transitionSkew - math.sin(p.transitionSkewSlope)*p.transitionSkewStrengthRoot
y4 = p.transitionSkew
skewPt = pow(tm1,3)*y1 + 3*pow(tm1,2)*t*y2 + 3*tm1*pow(t,2)*y3 + pow(t,3)*y4
skew.append(skewPt);
else:
#Using cubic spline interpolation.
t = (span-bladeTransition)/bladeLen
tm1 = 1-t
y1 = p.transitionChord
y2 = p.transitionChord + math.sin(p.transitionSlope)*p.transitionStrengthTip
y3 = p.tipChord - math.sin(p.tipSlope)*p.tipStrength
y4 = p.tipChord
chord = pow(tm1,3)*y1 + 3*pow(tm1,2)*t*y2 + 3*tm1*pow(t,2)*y3 + pow(t,3)*y4
chordArray.append(chord)
x1=0
x2=math.cos(p.transitionSlope)*p.transitionStrengthTip
x3=(bladeLen-math.cos(p.tipSlope)*p.tipStrength)
x4=bladeLen
x = pow(tm1,3)*x1 + 3*pow(tm1,2)*t*x2 + 3*tm1*pow(t,2)*x3 + pow(t,3)*x4
sPos.append(bladeTransition+x)
y1 = p.transitionThick
y2 = p.transitionThick + math.sin(p.rootThickSlope)*p.rootThickStrength
y3 = p.tipThick - math.sin(p.transitionThickSlope)*p.transitionThickStrengthTip
y4 = p.tipThick
thickPt = pow(tm1,3)*y1 + 3*pow(tm1,2)*t*y2 + 3*tm1*pow(t,2)*y3 + pow(t,3)*y4
NACAArray.append([5,3,int(thickPt*10),int(thickPt*100-int(thickPt*10)*10)])
y1 = p.transitionSkew
y2 = p.transitionSkew+ math.sin(p.transitionSkewSlope)*p.transitionSkewStrengthTip
y3 = p.tipSkew - math.sin(p.tipSkewSlope)*p.tipSkewStrength
y4 = p.tipSkew
skewPt = pow(tm1,3)*y1 + 3*pow(tm1,2)*t*y2 + 3*tm1*pow(t,2)*y3 + pow(t,3)*y4
skew.append(skewPt);
#error check of inputs
if(len(chordArray) != nspan or len(NACAArray) != nspan):
print("The size of the array of chord lengths or the array of airfoil NACA digits does not match the number of span points used to define the blade geometry.")
#Delete any existing prop geoms
DLUtils.DeleteMesh(propName)
#Generate Hub
DLUtils.DrawCylinder("Hub",hubDia,0,hubHeight,res)#use a 0.001m tolerance which we'll trim off.
cyl = bpy.data.objects["Hub"]
cyl.name = propName
cyl.data.name = propName
DLUtils.SelectOnly(propName)
bpy.ops.transform.rotate(value=math.radians(90),axis=(0.0,1.0,0.0))
DLUtils.MoveObject(propName,[2.0,0,0])
areaArray = []
#Generate vertex coordinates with twist and scale along the span
for i in range(0,nspan+1):
span = sPos[i] #i*dSpan
if(span == 0):
twistAngle = 0
elif(span < bladeTransition):
twistAngle = math.atan(pitch/(2*math.pi*span))*span/bladeTransition
else:
twistAngle = math.atan(pitch/(2*math.pi*span))
#get the airfoil profile vertices
tmpVerts = TurboMachLib.NACA4Profile(camber=NACAArray[i][0],thickness=NACAArray[i][2]*10+NACAArray[i][3],camberPos=NACAArray[i][1]*10,chord=chordArray[i],npts=npts)
areaArray.append(0);
centerOfTwist[0] = chordArray[i]*skew[i]
#centerOfTwist[1] = raiseFoil
for v in range(0,len(tmpVerts)):
#shift all verts for twisting
tmpVerts[v][0] -= centerOfTwist[0]
tmpVerts[v][1] -= centerOfTwist[1]
#Twist the airfoil vertices. First we shift them to get the desired center of rotation.
tmpVert[0] = tmpVerts[v][0]*math.cos(twistAngle) -tmpVerts[v][1]*math.sin(twistAngle)
tmpVert[1] = tmpVerts[v][0]*math.sin(twistAngle) +tmpVerts[v][1]*math.cos(twistAngle)
#shift all verts to their proper span location in Z
tmpVert[2] = span+0.01*bladeHeight #Shift blade by 1% of blade height to prevent poor boolean ops
#append the vert to the master vertex list
verts.append((tmpVert[0],tmpVert[1],tmpVert[2]))
if(v != 0):
dx = abs(verts[len(verts)-1][0] - verts[len(verts)-2][0])
dy = abs(verts[len(verts)-1][1] + verts[len(verts)-2][1])/2
areaArray[i] += dy*dx
#Generate Polies from vertex IDs
#Bottom Cap
faces.append((0,1,npts))
for i in range(1,npts-1):
faces.append((i,i+1,npts+i))
faces.append((i,npts+i,npts+i-1))
#Middle
nPerStage = npts*2-1
for j in range(0,nspan):
#Top Side
for i in range(0,npts-1):
faces.append((nPerStage*j+i,nPerStage*(j+1)+i,nPerStage*(j+1)+i+1))
faces.append((nPerStage*j+i,nPerStage*(j+1)+i+1,nPerStage*j+i+1))
#First strip for bottom side (hooks to verts from top side)
faces.append((nPerStage*j,nPerStage*(j+1)+npts,nPerStage*(j+1)))
faces.append((nPerStage*j,nPerStage*j+npts,nPerStage*(j+1)+npts))
#Rest of bottom side
for i in range(0,npts-2):
faces.append((nPerStage*j+i+npts,nPerStage*(j+1)+i+npts+1,nPerStage*(j+1)+i+npts))
faces.append((nPerStage*j+i+npts,nPerStage*j+i+npts+1,nPerStage*(j+1)+i+npts+1))
#Back face
faces.append((nPerStage*j+npts-1,nPerStage*(j+1)+npts-1,nPerStage*(j+1)+npts*2-2))
faces.append((nPerStage*j+npts-1,nPerStage*(j+1)+npts*2-2,nPerStage*(j)+npts*2-2))
#Top Cap
faces.append((nPerStage*(nspan),nPerStage*(nspan)+1,nPerStage*(nspan)+npts))
for i in range(1,npts-1):
faces.append((nPerStage*(nspan)+i,nPerStage*(nspan)+npts+i,nPerStage*(nspan)+i+1))
faces.append((nPerStage*(nspan)+i,nPerStage*(nspan)+npts+i-1,nPerStage*(nspan)+npts+i))
#Create Blender object for the blade
dAngle = 360.0/nBlades
for i in range(0,nBlades):
print("Draw Blade_" + str(i))
blade = DLUtils.createMesh("Blade_"+str(i), origin, verts, [], faces)
DLUtils.SelectOnly("Blade_"+str(i))
bpy.ops.transform.rotate(value=math.radians(90),axis=(0.0,0.0,1.0))
bpy.ops.transform.rotate(value=math.radians(dAngle)*i,axis=(1.0,0.0,0.0))
#Union the blades to the hub
for i in range(0,nBlades):
print("Union: Blade_" +str(i))
DLUtils.BooleanMesh(propName,"Blade_"+str(i),"UNION",True)
#trim the blades to hub height
DLUtils.DrawBox("box", hubDia*1.1,hubDia*1.1,hubDia*1.1)
DLUtils.MoveObject("box",[propDia/2+hubHeight/2+0.001,0,0])
DLUtils.BooleanMesh(propName,"box","DIFFERENCE",True)
#cut the axle hole
DLUtils.DrawCylinder("hole",axleDia,0,hubHeight*2,res)
DLUtils.SelectOnly("hole")
bpy.ops.transform.rotate(value=math.radians(90),axis=(0.0,1.0,0.0))
DLUtils.BooleanMesh(propName,"hole",'DIFFERENCE',True)
#Cut room for the axle shive
DLUtils.DrawCylinder("ShiveHole",(hubDia-axleDia)/4+axleDia,0,hubHeight/1.5,res)
DLUtils.SelectOnly("ShiveHole")
bpy.ops.transform.rotate(value=math.radians(90),axis=(0.0,1.0,0.0))
DLUtils.BooleanMesh(propName,"ShiveHole",'DIFFERENCE',True)
#DLUtils.MoveObject(propName,[2.0,0,0])
#trim the blades to the proper dia
DLUtils.DrawCylinder("BladeTrim",propDia,0,propDia,256)
DLUtils.SelectOnly("BladeTrim")
bpy.ops.transform.rotate(value=math.radians(90),axis=(0.0,1.0,0.0))
DLUtils.BooleanMesh(propName,"BladeTrim",'INTERSECT',True)
#done!
print((BladeAxialStress(sPos,areaArray, 40e6, 1300,15000)))
return
