Customizable Preprocessing
In this example, we show the third level of what is going on behind the precompiled binary This includes all of the second, but also breaks out the setupOWENS function. This would be a good starting point if you need to make modifications to use a unique mesh generation function, change how sectional properties are input, or adapt for a unique design an properly map the sectional properties to each element and apply unique boundary conditions, etc.
This example is also available as a Jupyter notebook todo: get link working:
This example is the same as example B except that the setupOWENS function is broken out and each step defined
import OWENS
import OWENSFEA
import OWENSAero
import QuadGK
import FLOWMath
import PyPlot
#### PyPlot.pygui(true)
import OWENSOpenFASTWrappers
runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1]
# runpath = path = splitdir(@__FILE__)[1]
Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml")
nothingUnpack inputs, or you could directly input them here and bypass the file
verbosity = 1
analysisType = Inp.analysisType
turbineType = Inp.turbineType
eta = Inp.eta
Nbld = Inp.Nbld
towerHeight = Inp.towerHeight
rho = Inp.rho
Vinf = Inp.Vinf
controlStrategy = Inp.controlStrategy
RPM = Inp.RPM
Nslices = Inp.Nslices
ntheta = Inp.ntheta
structuralModel = Inp.structuralModel
ntelem = Inp.ntelem
nbelem = Inp.nbelem
ncelem = Inp.ncelem
nselem = Inp.nselem
ifw = Inp.ifw
WindType = Inp.WindType
AModel = Inp.AModel
windINPfilename = "$(path)$(Inp.windINPfilename)"
ifw_libfile = Inp.ifw_libfile
if ifw_libfile == "nothing"
ifw_libfile = nothing
end
Blade_Height = Inp.Blade_Height
Blade_Radius = Inp.Blade_Radius
numTS = Inp.numTS
delta_t = Inp.delta_t
NuMad_geom_xlscsv_file_twr = "$(path)$(Inp.NuMad_geom_xlscsv_file_twr)"
NuMad_mat_xlscsv_file_twr = "$(path)$(Inp.NuMad_mat_xlscsv_file_twr)"
NuMad_geom_xlscsv_file_bld = "$(path)$(Inp.NuMad_geom_xlscsv_file_bld)"
NuMad_mat_xlscsv_file_bld = "$(path)$(Inp.NuMad_mat_xlscsv_file_bld)"
NuMad_geom_xlscsv_file_strut = "$(path)$(Inp.NuMad_geom_xlscsv_file_strut)"
NuMad_mat_xlscsv_file_strut = "$(path)$(Inp.NuMad_mat_xlscsv_file_strut)"
adi_lib = Inp.adi_lib
if adi_lib == "nothing"
adi_lib = nothing
end
adi_rootname = "$(path)$(Inp.adi_rootname)"
println("Set up Turbine")
AD15On = true
B = Nbld
R = Blade_Radius#177.2022*0.3048 #m
H = Blade_Height#1.02*R*2 #m
shapeZ = collect(LinRange(0,H,Nslices+1))
shapeX = R.*(1.0.-4.0.*(shapeZ/H.-.5).^2)
shapeY = zeros(Nslices+1)
stack_layers_bld = nothing
stack_layers_scale = [1.0,1.0]
chord_scale = [1.0,1.0]
thickness_scale = [1.0,1.0]
Htwr_base=towerHeight
strut_mountpointbot = 0.11
strut_mountpointtop = 0.89
joint_type = 0
c_mount_ratio = 0.05
angularOffset = -pi/2
custommesh = nothing
if AModel=="AD" #TODO: unify flag
AD15On=true #AD for AeroDyn, DMS for double multiple streamtube, AC for actuator cylinder
else
AD15On=false
end
DSModel="BV"
RPI=true
cables_connected_to_blade_base = true
meshtype = "Darrieus"
nothingSet up TurbineHere is where we take the inputs from setupOWENS and break out what is going on behind the function. We do some intermediate calculations on the blade shape and angles
Nstrutperbld = 2 #TODO: generalize and propogate
strut_twr_mountpoint = [0.25,0.75]
strut_bld_mountpoint = [0.25,0.75]
Nbld = B
H = maximum(shapeZ) #m,
Htwr_blds = H
AD15hubR = 0.1
R = maximum(shapeX) #m,
omega = RPM / 60 * 2 * pi
tsr = omega*R/Vinf
nothingHere we set up the mesh using one of the pre-made meshing functions. For this case, there is a function for the ARCUS, as well as for towered VAWTs where you can have an arbitrary blade shape with connected struts, and if the blade tips touch the tower, then you can tell it to constrain them to the tower thus allowing for both H-VAWT and Darrieus designs.
#########################################
### Set up mesh
#########################################
if meshtype == "ARCUS" && custommesh == nothing #TODO, for all of these propogate the AeroDyn additional output requirements
mymesh,myort,myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_arcus_mesh(;Htwr_base,
Hbld = H, #blade height
R, # m bade radius
nblade = Nbld,
ntelem, #tower elements
nbelem, #blade elements
ncelem,
c_mount_ratio,
bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above
bshapez = shapeZ,
AD15_ccw = true,
joint_type, #hinged about y axis
cables_connected_to_blade_base,
angularOffset) #Blade shape, magnitude is irrelevant, scaled based on height and radius above
elseif (meshtype == "Darrieus" || meshtype == "H-VAWT") && custommesh == nothing
if meshtype == "Darrieus"
connectBldTips2Twr = true
else
connectBldTips2Twr = false
end
mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_mesh_struts(;Htwr_base,
Htwr_blds,
Hbld = H, #blade height
R, # m bade radius
AD15hubR, #TODO: hook up with AD15 file generation
nblade = Nbld,
ntelem, #tower elements
nbelem, #blade elements
nselem,
strut_twr_mountpoint,
strut_bld_mountpoint,
bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above
bshapez = shapeZ,
bshapey = shapeY, # but magnitude for this is relevant
angularOffset, #Blade shape, magnitude is irrelevant, scaled based on height and radius above
AD15_ccw = true,
verbosity=0, # 0 nothing, 1 basic, 2 lots: amount of printed information
connectBldTips2Twr)
elseif custommesh != nothing
mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = custommesh(;Htwr_base,
Htwr_blds,
Hbld = H, #blade height
R, # m bade radius
AD15hubR, #TODO: hook up with AD15 file generation
nblade = Nbld,
ntelem, #tower elements
nbelem, #blade elements
nselem,
strut_twr_mountpoint,
strut_bld_mountpoint,
bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above
bshapez = shapeZ,
bshapey = shapeY, # but magnitude for this is relevant
angularOffset, #Blade shape, magnitude is irrelevant, scaled based on height and radius above
AD15_ccw = true,
verbosity=0, # 0 nothing, 1 basic, 2 lots: amount of printed information)
)
else #TODO unify with HAWT
error("please choose a valid mesh type (Darrieus, H-VAWT, ARCUS)")
end
nTwrElem = Int(mymesh.meshSeg[1])
try
if contains(NuMad_mat_xlscsv_file_bld,"34m") || meshtype == "ARCUS" #TODO: this is really odd,
nTwrElem = Int(mymesh.meshSeg[1])+1
end
catch
nTwrElem = Int(mymesh.meshSeg[1])
end
nothing┌ Warning: Assignment to `nTwrElem` in soft scope is ambiguous because a global variable by the same name exists: `nTwrElem` will be treated as a new local. Disambiguate by using `local nTwrElem` to suppress this warning or `global nTwrElem` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:211
┌ Warning: Assignment to `nTwrElem` in soft scope is ambiguous because a global variable by the same name exists: `nTwrElem` will be treated as a new local. Disambiguate by using `local nTwrElem` to suppress this warning or `global nTwrElem` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:214Here is a way that you can visualize the nodal numbers of the mesh
PyPlot.figure()
for icon = 1:length(mymesh.conn[:,1])
idx1 = mymesh.conn[icon,1]
idx2 = mymesh.conn[icon,2]
PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"k.-")
PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",ha="center",va="center")
#### sleep(0.1)
end
for ijoint = 1:length(myjoint[:,1])
idx2 = Int(myjoint[ijoint,2])
idx1 = Int(myjoint[ijoint,3])
PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"r.-")
PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",color="r",ha="center",va="center")
PyPlot.text3D(mymesh.x[idx2].+rand()/30,mymesh.y[idx2].+rand()/30,mymesh.z[idx2].+rand()/30,"$idx2",color="r",ha="center",va="center")
#### sleep(0.1)
end
PyPlot.xlabel("x")
PyPlot.ylabel("y")
PyPlot.zlabel("z")PyObject Text(0.5, 0, 'z')This is where the sectional properties for the tower are either read in from the file, or are directly input and could be manuplated here in the script
#########################################
### Set up Sectional Properties
#########################################
if !isnothing(NuMad_geom_xlscsv_file_twr)
numadIn_twr = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_twr;section=:tower)
else
n_web = 0
n_stack = 2
n_segments = 2
span = [0.0, 6.607421057, 13.21484211, 19.82226317, 26.42968423, 33.03710529, 39.64452634, 46.2519474, 52.85936846, 59.46678951, 66.07421057, 72.68163163, 79.28905268, 85.89647374, 92.5038948, 99.11131586, 105.7187369, 112.326158, 118.933579, 125.5410001, 132.1484211]
airfoil = ["circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular", "circular"]
te_type = ["round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round", "round"]
twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0]
chord = [10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 10.0, 0.25, 0.25, 0.25]
xoffset = [0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5, 0.5]
aerocenter = [0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25, 0.25]
stack_mat_types = [8, 2]
stack_layers = [70 3; 70 3; 70 3; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03; 30.303 3.03]
segments = [-1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0; -1.0 0.0 1.0]
DPtypes = ["" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""; "" "" ""]
skin_seq = [Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2]); Seq([2, 1, 2]) Seq([2, 1, 2])]
web_seq = Array{Seq, 2}(undef, length(twist_d),0) #can be any number of stack nums, so we have to make non-square containers
web_dp = Array{Seq, 2}(undef, length(twist_d),0) #this is fixed size square, but it's easier to do it this way
numadIn_twr = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp)
end
#### Add the full path
for (i,airfoil) in enumerate(numadIn_twr.airfoil)
numadIn_twr.airfoil[i] = "$path/airfoils/$airfoil"
end
nothingHere is where the material properties for the tower are either read in from the file, or directly input
if !isnothing(NuMad_mat_xlscsv_file_twr)
plyprops_twr = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_twr)
else
names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"]
plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e9, 1.0e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)]
plyprops_twr = OWENS.plyproperties(names,plies)
endOWENS.plyproperties(Any["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10"], Composites.Material{Float64}[Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5)], [2.06, 2.1, 2.21, 7.23, 2.06, 2.1, 7.23], [1.0e12 8.0e11 … 1.9999999999999997e11 0.0; 1.0e12 8.0e11 … 1.9999999999999997e11 0.0; … ; 1.0e12 8.0e11 … 1.9999999999999997e11 0.0; 1.0e12 8.0e11 … 1.9999999999999997e11 0.0], [0.0 1.4000000000000001 … 5.6000000000000005 7.0; 0.0 1.4000000000000001 … 5.6000000000000005 7.0; … ; 0.0 1.4000000000000001 … 5.6000000000000005 7.0; 0.0 1.4000000000000001 … 5.6000000000000005 7.0])Then this is where precomp.jl is called to get first the precomp outputs, then formatting those into the OWENS format, and then in the GXBeam.jl format for if GXBeam is used as the structural solver.
twr_precompoutput,twr_precompinput,lam_U_twr,lam_L_twr,lam_W_twr = OWENS.getOWENSPreCompOutput(numadIn_twr;plyprops = plyprops_twr)
sectionPropsArray_twr = OWENS.getSectPropsFromOWENSPreComp(LinRange(0,1,nTwrElem),numadIn_twr,twr_precompoutput;precompinputs=twr_precompinput)
stiff_twr, mass_twr = OWENS.getSectPropsFromOWENSPreComp(LinRange(0,1,nTwrElem),numadIn_twr,twr_precompoutput;GX=true)
nothingFor the blades, we repeat what was done for the tower, but also include some simple design options for scaling thicknesses,
if !isnothing(NuMad_geom_xlscsv_file_bld)
numadIn_bld = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_bld;section=:blade)
else
n_web = 1
n_stack = 7
n_segments = 12
span = [0.0, 6.607, 13.215, 19.822, 26.43, 33.037, 39.645, 46.252, 52.859, 59.467, 66.074, 72.682, 79.289, 85.896, 92.504, 99.111, 105.719, 112.326, 118.934, 125.541, 132.148]
airfoil = ["circular", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021"]
te_type = ["round", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp"]
twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0]
chord = [10.0, 10.0, 9.0, 8.0, 8.0, 7.0, 7.0, 6.0, 6.0, 6.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0]
xoffset = [0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3]
aerocenter = [0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2]
stack_mat_types = [8, 2, 4, 8, 8, 8, 4]
if isnothing(stack_layers_bld)
stack_layers = [30.0 2.0 15.0 25.0 25.0 2.0 13.0; 15.0 2.0 10.0 13.0 11.0 2.0 11.0; 10.0 1.0 8.0 10.0 10.0 2.0 10.0; 8.0 1.0 6.0 9.0 10.0 1.0 9.0; 7.0 1.0 5.0 8.0 9.0 1.0 7.0; 6.0 1.0 4.0 8.0 9.0 1.0 6.0; 6.0 1.0 4.0 8.0 8.0 1.0 5.0; 6.0 1.0 4.0 7.0 7.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 7.0 8.0 3.0 5.0; 7.0 2.0 3.0 9.0 12.0 3.0 6.0; 10.0 3.0 4.0 11.0 15.0 3.0 6.0; 12.0 3.0 4.0 13.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 10.0 1.0 4.0 10.0 12.0 1.0 5.0]
else
stack_layers = stack_layers_bld
end
segments = [-1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0]
DPtypes = ["" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""]
skin_seq = [Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2])]
web_seq = [Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]);;]
web_dp = [Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]);;]
numadIn_bld = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp)
end
for icol = 1:length(numadIn_bld.stack_layers[1,:])
numadIn_bld.stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_bld.chord))
end
numadIn_bld.chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_bld.chord))
for (i,airfoil) in enumerate(numadIn_bld.airfoil)
numadIn_bld.airfoil[i] = "$path/airfoils/$airfoil"
end
if !isnothing(NuMad_mat_xlscsv_file_bld)
plyprops_bld = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_bld)
else
names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"]
plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)]
plyprops_bld = OWENS.plyproperties(names,plies)
end
bld1start = Int(mymesh.structuralNodeNumbers[1,1]) #Get blade spanwise position
bld1end = Int(mymesh.structuralNodeNumbers[1,end])
spanpos = [0.0;cumsum(sqrt.(diff(mymesh.x[bld1start:bld1end]).^2 .+ diff(mymesh.z[bld1start:bld1end]).^2))]
if length(thickness_scale)==2
yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_bld.span)))
elseif length(thickness_scale)==length(numadIn_bld.span)
yscale = thickness_scale
end
bld_precompoutput,bld_precompinput,lam_U_bld,lam_L_bld,lam_W_bld = OWENS.getOWENSPreCompOutput(numadIn_bld;yscale,plyprops = plyprops_bld)
sectionPropsArray_bld = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_bld,bld_precompoutput;precompinputs=bld_precompinput)
stiff_bld, mass_bld = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_bld,bld_precompoutput;GX=true)
nothing┌ Warning: Data for SN curve control points not found in material file columns 23:28 for stress in Mpa, 29:33 for cycles in log10
└ @ OWENS ~/work/OWENS.jl/OWENS.jl/src/fileio.jl:648Similarly for the struts, we do what was done for the blades
numadIn_strut = Array{OWENS.NuMad, 1}(undef, Nstrutperbld)
strut_precompoutput = Array{Array{OWENS.OWENSPreComp.Output, 1},1}(undef, Nstrutperbld)
strut_precompinput = Array{Array{OWENS.OWENSPreComp.Input, 1},1}(undef, Nstrutperbld)
plyprops_strut = Array{OWENS.plyproperties, 1}(undef, Nstrutperbld)
lam_U_strut = Array{Array{OWENS.Composites.Laminate, 2}}(undef, Nstrutperbld)
lam_L_strut = Array{Array{OWENS.Composites.Laminate, 2}}(undef, Nstrutperbld)
lam_W_strut = Array{Array{OWENS.Composites.Laminate, 2}}(undef, Nstrutperbld)
sectionPropsArray_strut = Array{Array{OWENSFEA.SectionPropsArray, 1}}(undef, Nstrutperbld)
stiff_strut = Array{Array{Array{Float64,2}, 1},1}(undef, Nstrutperbld)
mass_strut = Array{Array{Array{Float64,2}, 1},1}(undef, Nstrutperbld)
for istrut = 1:Nstrutperbld
if !isnothing(NuMad_geom_xlscsv_file_strut)
if typeof(NuMad_geom_xlscsv_file_strut)==String
numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut)
elseif typeof(NuMad_geom_xlscsv_file_strut) == OrderedCollections.OrderedDict{Symbol, Any}
if length(NuMad_geom_xlscsv_file_strut[:components][:struts])==1
numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut;section=:struts,subsection=1)
else
numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut;section=:struts,subsection=istrut)
end
else
numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut[istrut])
end
else
n_web = 1
n_stack = 7
n_segments = 12
span = [0.0, 6.607, 13.215, 19.822, 26.43, 33.037, 39.645, 46.252, 52.859, 59.467, 66.074, 72.682, 79.289, 85.896, 92.504, 99.111, 105.719, 112.326, 118.934, 125.541, 132.148]
airfoil = ["circular", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021"]
te_type = ["round", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp"]
twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0]
chord = [10.0, 10.0, 9.0, 8.0, 8.0, 7.0, 7.0, 6.0, 6.0, 6.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0]
xoffset = [0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3]
aerocenter = [0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2]
stack_mat_types = [8, 2, 4, 8, 8, 8, 4]
if isnothing(stack_layers_strut)
stack_layers = [30.0 2.0 15.0 25.0 25.0 2.0 13.0; 15.0 2.0 10.0 13.0 11.0 2.0 11.0; 10.0 1.0 8.0 10.0 10.0 2.0 10.0; 8.0 1.0 6.0 9.0 10.0 1.0 9.0; 7.0 1.0 5.0 8.0 9.0 1.0 7.0; 6.0 1.0 4.0 8.0 9.0 1.0 6.0; 6.0 1.0 4.0 8.0 8.0 1.0 5.0; 6.0 1.0 4.0 7.0 7.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 7.0 8.0 3.0 5.0; 7.0 2.0 3.0 9.0 12.0 3.0 6.0; 10.0 3.0 4.0 11.0 15.0 3.0 6.0; 12.0 3.0 4.0 13.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 10.0 1.0 4.0 10.0 12.0 1.0 5.0]
else
stack_layers = stack_layers_strut
end
segments = [-1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0]
DPtypes = ["" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""]
skin_seq = [Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2])]
web_seq = [Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]);;]
web_dp = [Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]);;]
numadIn_strut[istrut] = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp)
end
for icol = 1:length(numadIn_strut[istrut].stack_layers[1,:])
numadIn_strut[istrut].stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_strut[istrut].chord))
end
#### numadIn_strut[istrut].chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut[istrut].chord))
for (i,airfoil) in enumerate(numadIn_strut[istrut].airfoil)
numadIn_strut[istrut].airfoil[i] = "$path/airfoils/$airfoil"
end
if !isnothing(NuMad_mat_xlscsv_file_strut)
plyprops_strut[istrut] = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_strut)
else
names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"]
plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)]
plyprops_strut[istrut] = OWENS.plyproperties(names,plies)
end
#### TODO: not straight struts
spanpos = LinRange(0,1,nselem+1)#[0.0;cumsum(sqrt.(diff(mymesh.x[strut1start:strut1end]).^2 .+ diff(mymesh.z[strut1start:strut1end]).^2))]
if length(thickness_scale)==2
yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_strut[istrut].span)))
elseif length(thickness_scale)==length(numadIn_strut[istrut].span)
yscale = thickness_scale
end
strut_precompoutput[istrut],strut_precompinput[istrut],lam_U_strut[istrut],lam_L_strut[istrut],lam_W_strut[istrut] = OWENS.getOWENSPreCompOutput(numadIn_strut[istrut];yscale,plyprops = plyprops_strut[istrut])
sectionPropsArray_strut[istrut] = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut[istrut],strut_precompoutput[istrut];precompinputs=strut_precompinput[istrut])
stiff_strut[istrut], mass_strut[istrut] = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut[istrut],strut_precompoutput[istrut];GX=true)
end
nothing┌ Warning: Assignment to `spanpos` in soft scope is ambiguous because a global variable by the same name exists: `spanpos` will be treated as a new local. Disambiguate by using `local spanpos` to suppress this warning or `global spanpos` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:439
┌ Warning: Assignment to `yscale` in soft scope is ambiguous because a global variable by the same name exists: `yscale` will be treated as a new local. Disambiguate by using `local yscale` to suppress this warning or `global yscale` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:442
┌ Warning: Data for SN curve control points not found in material file columns 23:28 for stress in Mpa, 29:33 for cycles in log10
└ @ OWENS ~/work/OWENS.jl/OWENS.jl/src/fileio.jl:648
┌ Warning: Data for SN curve control points not found in material file columns 23:28 for stress in Mpa, 29:33 for cycles in log10
└ @ OWENS ~/work/OWENS.jl/OWENS.jl/src/fileio.jl:648Here we combine the section properties into an array matching the mesh elements
bldssecprops = collect(Iterators.flatten(fill(sectionPropsArray_bld, Nbld)))
#### strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld)))
if meshtype == "ARCUS"
sectionPropsArray = [sectionPropsArray_twr; bldssecprops]#; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str]
stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld)))
stiff_array = [stiff_twr; stiff_blds]#; stiff_struts]
mass_blds = collect(Iterators.flatten(fill(mass_bld, Nbld)))
mass_array = [mass_twr; mass_blds]#; mass_struts]
for icable = 1:Nbld
sectionPropsArray = [sectionPropsArray; sectionPropsArray_strut[1]]
stiff_array = [stiff_array;stiff_strut[1]]
mass_array = [mass_array;mass_strut[1]]
end
else
sectionPropsArray = [sectionPropsArray_twr; bldssecprops]#; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str]
stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld)))
stiff_array = [stiff_twr; stiff_blds]#; stiff_struts]
mass_blds = collect(Iterators.flatten(fill(mass_bld, Nbld)))
mass_array = [mass_twr; mass_blds]#; mass_struts]
for istrut = 1:Nstrutperbld
for ibld = 1:Nbld
global sectionPropsArray = [sectionPropsArray; sectionPropsArray_strut[istrut]]
global stiff_array = [stiff_array;stiff_strut[istrut]]
global mass_array = [mass_array;mass_strut[istrut]]
end
end
end
rotationalEffects = ones(mymesh.numEl) #TODO: non rotating tower, or rotating blades
if length(sectionPropsArray)<mymesh.numEl
@warn "There are more mesh elements than sectional properties, applying the last strut's sectional properties to the remaining"
n_diff = mymesh.numEl - length(sectionPropsArray)
sectionPropsArray = [sectionPropsArray; fill(sectionPropsArray_strut[end][2],n_diff)]
stiff_array = [stiff_array;fill(stiff_strut[end][2],n_diff)]
mass_array = [mass_array;fill(mass_strut[end][2],n_diff)]
end
#### store data in element object
myel = OWENSFEA.El(sectionPropsArray,myort.Length,myort.Psi_d,myort.Theta_d,myort.Twist_d,rotationalEffects)
system, assembly, sections = OWENS.owens_to_gx(mymesh,myort,myjoint,sectionPropsArray,stiff_array,mass_array)
nothing┌ Warning: Assignment to `sectionPropsArray` in soft scope is ambiguous because a global variable by the same name exists: `sectionPropsArray` will be treated as a new local. Disambiguate by using `local sectionPropsArray` to suppress this warning or `global sectionPropsArray` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:471
┌ Warning: Assignment to `stiff_array` in soft scope is ambiguous because a global variable by the same name exists: `stiff_array` will be treated as a new local. Disambiguate by using `local stiff_array` to suppress this warning or `global stiff_array` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:472
┌ Warning: Assignment to `mass_array` in soft scope is ambiguous because a global variable by the same name exists: `mass_array` will be treated as a new local. Disambiguate by using `local mass_array` to suppress this warning or `global mass_array` to assign to the existing global variable.
└ @ C_customizablePreprocessing.md:473Set up the OWENSAero aerodynamics if used
if !AD15On
#########################################
### Set up aero forces
#########################################
#### translate from blade span to blade height between the numad definition and the vertical slice positions
#### First get the angles from the overall geometry npoints and go to the numad npoints
delta_xs = shapeX[2:end] - shapeX[1:end-1]
delta_zs = shapeZ[2:end] - shapeZ[1:end-1]
delta3D = atan.(delta_xs./delta_zs)
delta3D_spl = safeakima(shapeZ[1:end-1]./maximum(shapeZ[1:end-1]), delta3D,LinRange(0,1,length(numadIn_bld.span)-1))
#### now convert the numad span to a height
bld_height_numad = cumsum(diff(numadIn_bld.span).*(1.0.-abs.(sin.(delta3D_spl))))
bld_height_numad_unit = bld_height_numad./maximum(bld_height_numad)
#### now we can use it to access the numad data
chord = safeakima(bld_height_numad_unit, numadIn_bld.chord,LinRange(bld_height_numad_unit[1],1,Nslices))
airfoils = fill("nothing",Nslices)
twist = safeakima(bld_height_numad_unit, numadIn_bld.twist_d.*pi/180,LinRange(bld_height_numad_unit[1],1,Nslices))
#### Discretely assign the airfoils
for (iheight_numad,height_numad) in enumerate(bld_height_numad_unit)
for (iheight,height_slices) in enumerate(collect(LinRange(0,1,Nslices)))
if airfoils[iheight]=="nothing" && height_slices<=height_numad
airfoils[iheight] = "$(numadIn_bld.airfoil[iheight_numad]).dat"
end
end
end
OWENSAero.setupTurb(shapeX,shapeZ,B,chord,tsr,Vinf;AModel,DSModel,
afname = airfoils,
bld_y = shapeY,
rho,
twist, #TODO: verify twist is in same direction
mu,
eta,
ifw, #TODO: propogate WindType
turbsim_filename = windINPfilename,
ifw_libfile,
tau = [1e-5,1e-5],
AM_flag,
rotAccel_flag,
buoy_flag,
ntheta,
Nslices,
RPI)
aeroForcesACDMS(t,azi) = OWENS.mapACDMS(t,azi,mymesh,myel,OWENSAero.AdvanceTurbineInterpolate;alwaysrecalc=true)
deformAeroACDMS = OWENSAero.deformTurb
end
nothingSet up AeroDyn if used Here we create AeroDyn the files, first by specifying the names, then by creating the files, TODO: hook up the direct sectionPropsArray_str Then by initializing AeroDyn and grabbing the backend functionality with a function handle
if AD15On
ad_input_file = "$path/ADInputFile_SingleTurbine2.dat"
ifw_input_file = "$path/IW2.dat"
OLAF_filename = "$path/OLAF2.dat"
NumADBldNds = NumADStrutNds = 10
bldchord_spl = OWENS.safeakima(numadIn_bld.span./maximum(numadIn_bld.span), numadIn_bld.chord,LinRange(0,1,NumADBldNds))
#### Discretely assign the blade airfoils based on the next closest neighbor
bld_airfoil_filenames = fill("nothing",NumADBldNds) #TODO: cable drag?
for (ispan_numad,span_numad) in enumerate(numadIn_bld.span./maximum(numadIn_bld.span))
for (ispan,span_slices) in enumerate(collect(LinRange(0,1,NumADBldNds)))
if bld_airfoil_filenames[ispan]=="nothing" && span_slices<=span_numad
bld_airfoil_filenames[ispan] = "$(numadIn_bld.airfoil[ispan_numad]).dat"
end
end
end
if meshtype == "ARCUS"
blade_filenames = ["$path/blade$i.dat" for i=1:Nbld]
blade_chords = [bldchord_spl for i=1:Nbld]
blade_Nnodes = [NumADBldNds for i=1:Nbld]
airfoil_filenames = [bld_airfoil_filenames for i=1:Nbld]
else
blade_filenames = ["$path/blade$i.dat" for i=1:Nbld]
blade_chords = [bldchord_spl for i=1:Nbld]
blade_Nnodes = [NumADBldNds for i=1:Nbld]
airfoil_filenames = collect(Iterators.flatten([bld_airfoil_filenames for i=1:Nbld]))
for istrut = 1:Nstrutperbld
strutchord_spl = OWENS.safeakima(numadIn_strut[istrut].span./maximum(numadIn_strut[istrut].span), numadIn_strut[istrut].chord,LinRange(0,1,NumADStrutNds))
for ibld = 1:Nbld
global blade_filenames = [blade_filenames;"$path/strut$(istrut)_bld$ibld.dat"]
global blade_chords = [blade_chords;[strutchord_spl]]
global blade_Nnodes = [blade_Nnodes;NumADStrutNds]
#### Discretely assign the strut airfoils based on the next closest neighbor
strut_airfoil_filenames = fill("nothing",NumADStrutNds)
for (ispan_numad,span_numad) in enumerate(numadIn_strut[istrut].span./maximum(numadIn_strut[istrut].span))
for (ispan,span_slices) in enumerate(collect(LinRange(0,1,NumADBldNds)))
if strut_airfoil_filenames[ispan]=="nothing" && span_slices<=span_numad
strut_airfoil_filenames[ispan] = "$(numadIn_strut[istrut].airfoil[ispan_numad]).dat"
end
end
end
global airfoil_filenames = [airfoil_filenames; strut_airfoil_filenames]
end
end
end
OWENSOpenFASTWrappers.writeADinputFile(ad_input_file,blade_filenames,airfoil_filenames,OLAF_filename)
NumADBody = length(AD15bldNdIdxRng[:,1])
bld_len = zeros(NumADBody)
#### bladefileissaved = false
for (iADBody,filename) in enumerate(blade_filenames)
strt_idx = AD15bldNdIdxRng[iADBody,1]
end_idx = AD15bldNdIdxRng[iADBody,2]
if end_idx<strt_idx
tmp_end = end_idx
end_idx = strt_idx
strt_idx = tmp_end
end
#### Get the blade length
x1 = mymesh.x[strt_idx]
x2 = mymesh.x[end_idx]
y1 = mymesh.y[strt_idx]
y2 = mymesh.y[end_idx]
z1 = mymesh.z[strt_idx]
z2 = mymesh.z[end_idx]
bld_len[iADBody] = sqrt((x2-x1)^2+(y2-y1)^2+(z2-z1)^2)
#### Get the blade shape
ADshapeZ = collect(LinRange(0,H,NumADBldNds))
xmesh = mymesh.x[strt_idx:end_idx]
ymesh = mymesh.y[strt_idx:end_idx]
ADshapeX = sqrt.(xmesh.^2 .+ ymesh.^2)
ADshapeX .-= ADshapeX[1] #get it starting at zero #TODO: make robust for blades that don't start at 0
ADshapeXspl = OWENS.safeakima(LinRange(0,H,length(ADshapeX)),ADshapeX,ADshapeZ)
if iADBody<=Nbld #&& !bladefileissaved#Note that the blades can be curved and are assumed to be oriented vertically
#### bladefileissaved = true
BlSpn0=ADshapeZ
BlCrvAC0=ADshapeXspl
bladeangle = (iADBody-1)*2.0*pi/Nbld + angularOffset #TODO: pitch offset and twist offset that isn't from the helical
BlSpn = ADshapeZ
blade_twist = atan.(xmesh,ymesh).-bladeangle
#### TODO: reevalueate these equations and make sure they are robust against varying designs
BlCrvACinput = -ymesh.*sin(bladeangle).+xmesh.*cos(bladeangle)
BlCrvACinput = BlCrvACinput .- BlCrvACinput[1]
BlSwpAC = -OWENS.safeakima(LinRange(0,H,length(BlCrvACinput)),BlCrvACinput,ADshapeZ)
BlSwpACinput = xmesh.*sin(bladeangle).+ymesh.*cos(bladeangle)
BlSwpACinput = BlSwpACinput .- BlSwpACinput[1]
BlCrvAC = OWENS.safeakima(LinRange(0,H,length(BlSwpACinput)),BlSwpACinput,ADshapeZ)
BlCrvAng = zeros(blade_Nnodes[iADBody])
BlTwistinput =(blade_twist.-blade_twist[1])*180/pi
BlTwist = OWENS.safeakima(LinRange(0,H,length(BlTwistinput)),BlTwistinput,ADshapeZ)
BlChord=blade_chords[iADBody]
BlAFID=collect((iADBody-1)*NumADBldNds+1:iADBody*NumADBldNds)
elseif iADBody>Nbld # while the arms/struts are assumed to be straight and are oriented by the mesh angle
BlSpn=collect(LinRange(0,bld_len[iADBody],blade_Nnodes[iADBody]))
BlCrvAC=zeros(blade_Nnodes[iADBody])
BlSwpAC=zeros(blade_Nnodes[iADBody])
BlCrvAng=zeros(blade_Nnodes[iADBody])
BlTwist=zeros(blade_Nnodes[iADBody])
BlChord=blade_chords[iADBody]
BlAFID=collect((iADBody-1)*NumADStrutNds+1:iADBody*NumADStrutNds)
end
OWENSOpenFASTWrappers.writeADbladeFile(filename;NumBlNds=blade_Nnodes[iADBody],BlSpn,BlCrvAC,BlSwpAC,BlCrvAng,BlTwist,BlChord,BlAFID)
end
OWENSOpenFASTWrappers.writeOLAFfile(OLAF_filename;nNWPanel=200,nFWPanels=10)
OWENSOpenFASTWrappers.writeIWfile(Vinf,ifw_input_file;windINPfilename)
OWENSOpenFASTWrappers.setupTurb(adi_lib,ad_input_file,ifw_input_file,adi_rootname,[shapeX],[shapeZ],[B],[Htwr_base],[mymesh],[myort],[AD15bldNdIdxRng],[AD15bldElIdxRng];
rho = rho,
adi_dt = delta_t,
adi_tmax= numTS*delta_t,
omega = [omega],
adi_wrOuts = 1, # write output file [0 none, 1 txt, 2 binary, 3 both]
adi_DT_Outs = delta_t, # output frequency
numTurbines = 1,
refPos=[[0,0,0]],
hubPos=[[0,0,0.0]],
hubAngle=[[0,0,0]],
nacPos=[[0,0,0]],
adi_nstrut=[Nstrutperbld],
adi_debug=0,
isHAWT = false # true for HAWT, false for crossflow or VAWT
)
aeroForcesAD(t,azi) = OWENS.mapAD15(t,azi,[mymesh],OWENSOpenFASTWrappers.advanceAD15;alwaysrecalc=true,verbosity=1)
deformAeroAD=OWENSOpenFASTWrappers.deformAD15
end
nothingOpening AeroDyn-Inflow library at: /home/runner/.julia/packages/OWENSOpenFASTWrappers/OOzCv/src/../deps/openfast/build/modules/aerodyn/libaerodyn_inflow_c_binding
**************************************************************************************************
AeroDyn-Inflow library
Copyright (C) 2024 National Renewable Energy Laboratory
Copyright (C) 2024 Envision Energy USA LTD
This program is licensed under Apache License Version 2.0 and comes with ABSOLUTELY NO WARRANTY.
See the "LICENSE" file distributed with this software for details.
**************************************************************************************************
AeroDyn-Inflow library--128-NOTFOUND
Compile Info:
- Compiler: GCC version 11.4.0
- Architecture: 64 bit
- Precision: double
- OpenMP: Yes, number of threads: 4/4
- Date: Oct 17 2024
- Time: 21:57:44
Execution Info:
- Date: 10/17/2024
- Time: 22:15:41+0000
Running ADI.
Running AeroDyn.
Running OLAF.
- Directory: /home/runner/work/OWENS.jl/OWENS.jl/docs/build/examples
- RootName: /home/runner/work/OWENS.jl/OWENS.jl/examples/literate/ExampleB.
- Reading advanced options for OLAF:
[WARN] Line ignored: "VERT2" DEFAULT -10 30. 400 5. 5. 1 5.136 15.136 100
- OLAF regularization parameters (for wing 1):
WingReg (min/max) : 12.2425 25.2472
WakeReg (min/max) : 12.2425 25.2472
k = alpha delta nu: 0.0368
Running InflowWind.Calculate mass breakout of each material
mass_breakout_bld = OWENS.get_material_mass(plyprops_bld,numadIn_bld)
mass_breakout_blds = mass_breakout_bld.*length(mymesh.structuralNodeNumbers[:,1])
mass_breakout_twr = OWENS.get_material_mass(plyprops_twr,numadIn_twr;int_start=0.0,int_stop=Htwr_base)
################################
##### End setupOWENS
################################
nothingThen the rest of this example is the same as example B
if verbosity>0
println("\nBlades' Mass Breakout")
for (i,name) in enumerate(plyprops_bld.names)
println("$name $(mass_breakout_blds[i]) kg, $(plyprops_bld.costs[i]) \$/kg: \$$(mass_breakout_blds[i]*plyprops_bld.costs[i])")
end
println("\nTower Mass Breakout")
for (i,name) in enumerate(plyprops_twr.names)
println("$name $(mass_breakout_twr[i]) kg, $(plyprops_twr.costs[i]) \$/kg: \$$(mass_breakout_twr[i]*plyprops_twr.costs[i])")
end
println("Total Material Cost Blades: \$$(sum(mass_breakout_blds.*plyprops_bld.costs))")
println("Total Material Cost Tower: \$$(sum(mass_breakout_twr.*plyprops_twr.costs))")
println("Total Material Cost: \$$(sum(mass_breakout_blds.*plyprops_bld.costs)+ sum(mass_breakout_twr.*plyprops_twr.costs))")
end
pBC = [1 1 0
1 2 0
1 3 0
1 4 0
1 5 0
1 6 0]
inputs = OWENS.Inputs(;analysisType = structuralModel,
tocp = [0.0,100000.1],
Omegaocp = [RPM,RPM] ./ 60,
tocp_Vinf = [0.0,100000.1],
Vinfocp = [Vinf,Vinf],
numTS,
delta_t,
AD15On,
aeroLoadsOn = 2)
feamodel = OWENS.FEAModel(;analysisType = structuralModel,
outFilename = "none",
joint = myjoint,
platformTurbineConnectionNodeNumber = 1,
pBC,
nlOn = true,
numNodes = mymesh.numNodes,
RayleighAlpha = 0.05,
RayleighBeta = 0.05,
iterationType = "DI")
println("Running Unsteady")
if AD15On
t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist,
FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist,
epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly,
topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForcesAD,deformAero=deformAeroAD)
else
t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist,
FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist,
epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly,
topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForcesACDMS,deformAero=deformAeroACDMS)
end
if AD15On #TODO: move this into the run functions
OWENSOpenFASTWrappers.endTurb()
end
println("Saving VTK time domain files")
OWENS.OWENSFEA_VTK("$path/vtk/SNLARCUS5MW_timedomain_TNBnltrue",t,uHist,system,assembly,sections;scaling=1,azi=aziHist)
##########################################
#### Ultimate Failure #####
##########################################
massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU,
SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L,
topstrainout_tower_U,topstrainout_tower_LtopDamage_blade_U,
topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput,
bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld,
twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr,
mymesh,myel,myort,Nbld,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist,
kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1,
LE_U_idx=1,TE_U_idx=6,SparCapU_idx=3,ForePanelU_idx=2,AftPanelU_idx=5,
LE_L_idx=1,TE_L_idx=6,SparCapL_idx=3,ForePanelL_idx=2,AftPanelL_idx=5,
Twr_LE_U_idx=1,Twr_LE_L_idx=1,
AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing,strut_precompinput,plyprops_strut,numadIn_strut,lam_U_strut,lam_L_strut) #TODO: add in ability to have material safety factors and load safety factors
nothing
Blades' Mass Breakout
CLA_5500 20670.29648289118 kg, 2.06 $/kg: $42580.81075475583
CBX_2400 9730.417758654583 kg, 2.1 $/kg: $20433.877293174624
ETLX_2400 0.0 kg, 2.21 $/kg: $0.0
Airex_C70_55 789.5974763487575 kg, 7.23 $/kg: $5708.7897540015165
EBX_2400_x10 0.0 kg, 2.06 $/kg: $0.0
ETLX_2400_x10 0.0 kg, 2.1 $/kg: $0.0
Airex_C70_55_x10 0.0 kg, 7.23 $/kg: $0.0
Tower Mass Breakout
CLA_5500 4992.974575844168 kg, 2.06 $/kg: $10285.527626238985
CBX_2400 1217.5626883060443 kg, 2.1 $/kg: $2556.881645442693
ETLX_2400 0.0 kg, 2.21 $/kg: $0.0
Airex_C70_55 0.0 kg, 7.23 $/kg: $0.0
EBX_2400_x10 0.0 kg, 2.06 $/kg: $0.0
ETLX_2400_x10 0.0 kg, 2.1 $/kg: $0.0
Airex_C70_55_x10 0.0 kg, 7.23 $/kg: $0.0
Total Material Cost Blades: $68723.47780193196
Total Material Cost Tower: $12842.409271681678
Total Material Cost: $81565.88707361365
Running Unsteady
Running in specified rotor speed mode
Simulation Time: 0.0 seconds of 0.49 seconds
[INFO] FVW: Update States: reevaluation at the same starting time. This will not print on
subsequent occurences.
Simulation Time: 0.1 seconds of 0.49 seconds
Simulation Time: 0.2 seconds of 0.49 seconds
Simulation Time: 0.3 seconds of 0.49 seconds
Simulation Time: 0.4 seconds of 0.49 seconds
Simulation Complete.
>>> FINAL WRITE
Saving VTK time domain files
Composite Ultimate and Buckling Safety Factors
UPPER BLADE SURFACE
Minimum Safety Factor on Surface: 0.396100421933815
At time 0.035s at composite station 6 of 21 at lam 6 of 6
Maximum Damage per hr: 0.6612244898596223
At composite station 17 of 21 at lam 3 of 6
LOWER BLADE SURFACE
Minimum Safety Factor on Surface: 0.39579813639499317
At time 0.035s at composite station 6 of 21 at lam 6 of 6
Maximum Damage per hr: 0.7346938775726081
At composite station 9 of 21 at lam 4 of 6
UPPER TOWER
Minimum Safety Factor on tower Surface: 4.716031187784399
At time 0.049s at composite station 8 of 21 at lam 1 of 1
Maximum Damage per hr: 0.22040816348139644
At composite station 4 of 21 at lam 1 of 1
Lower TOWER
Minimum Safety Factor on tower Surface: 4.331286121960938
At time 0.035s at composite station 1 of 21 at lam 1 of 1
Maximum Damage per hr: 0.14693877554749607
At composite station 12 of 21 at lam 1 of 1This page was generated using Literate.jl.