Add examples for 5m and RM2

.gitignore

@@ -15,3 +15,6 @@ theta*
 *.docx
 *.csv
 *Manual*
+*.vscode
+*.png
+*.pdf

examples/RM2/.gitignore

@@ -0,0 +1,3 @@
+*.ech
+*.sum
+/vtk*

examples/RM2/RM2_medium.jl

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+import PyPlot
+PyPlot.rc("figure", figsize=(4, 3))
+PyPlot.rc("font", size=10.0)
+PyPlot.rc("lines", linewidth=1.5)
+PyPlot.rc("lines", markersize=3.0)
+PyPlot.rc("legend", frameon=false)
+PyPlot.rc("axes.spines", right=false, top=false)
+PyPlot.rc("figure.subplot", left=.18, bottom=.17, top=0.9, right=.9)
+PyPlot.rc("figure",max_open_warning=500)
+color_cycle=["#348ABD", "#A60628", "#009E73", "#7A68A6", "#D55E00", "#CC79A7"]
+PyPlot.pygui(true)
+# PyPlot.close("all")
+import OWENSAero
+using Test
+import HDF5
+import FLOWMath
+using Statistics:mean
+import DelimitedFiles
+
+path,_ = splitdir(@__FILE__)
+
+radius = 0.538
+height = 0.807
+chordmid = 0.066667
+chordtip = 0.04
+B = 3
+
+RE_d = [0.9,1.3]
+# for (ire,Vinf) in enumerate([0.8,1.2])
+    ire = 2
+    Vinf = 1.2
+    rho=1000.0
+    mu=1.792E-3
+    eta=0.5
+
+    ntheta = 30
+    Nslices = 30
+    ifw=false
+    AModel = "AC"
+
+    AM_flag = true
+    rotAccel_flag = true
+
+    chord = FLOWMath.akima([0.0,0.5,1.0],[chordtip,chordmid,chordtip],LinRange(0,1,Nslices))
+
+    # PyPlot.figure()
+    # PyPlot.plot(collect(LinRange(0,1,Nslices)),chord)
+
+    shapeX = ones(Nslices).*radius
+    shapeZ = LinRange(0,height,Nslices)
+
+
+    OWENSAero.setupTurb(shapeX,shapeZ,B,chord,10.0,Vinf;rho,mu,eta,afname = "$(path)/airfoils/NACA_0021.dat",DSModel="BV",Nslices,AM_flag,rotAccel_flag)
+
+    TSRrange = LinRange(1.0,5.0,15)
+    CP = zeros(length(TSRrange))
+    RpSteady = zeros(B,Nslices,ntheta,length(TSRrange))
+    TpSteady = zeros(B,Nslices,ntheta,length(TSRrange))
+    alphaSteady = zeros(B,Nslices,ntheta,length(TSRrange))
+    for (iTSR,TSR) in enumerate(collect(TSRrange))
+        # iTSR = 1
+        # TSR = 2.2
+        #Steady State Test
+        omega = Vinf/radius*TSR
+
+        RPM = omega * 60 / (2*pi)
+
+        CPSteady,
+        RpSteady[:,:,:,iTSR],
+        TpSteady[:,:,:,iTSR],
+        ZpSteady,
+        alphaSteady[:,:,:,iTSR],
+        cl_afSteady,
+        cd_afSteady,
+        VlocSteady,
+        ReSteady,
+        thetavecSteady,
+        nstepSteady,
+        Fx_baseSteady,
+        Fy_baseSteady,
+        Fz_baseSteady,
+        Mx_baseSteady,
+        My_baseSteady,
+        Mz_baseSteady,
+        powerSteady,
+        power2Steady,torque,z3Dnorm,delta,Mz_base2,M_addedmass_Np,
+        M_addedmass_Tp,F_addedmass_Np,F_addedmass_Tp = OWENSAero.steadyTurb(;omega,Vinf)
+
+        println("RPM: $RPM")
+        # println(mean(ReSteady))
+        area = height * radius*2
+
+        CP[iTSR] = powerSteady/(0.5*rho*Vinf^3*area)
+    end
+
+    PyPlot.figure("CP")
+    PyPlot.plot(TSRrange,CP,"-",color=color_cycle[2],label="OWENS Aero, $(RE_d[ire]) RE_d (No Added Mass)") #,color=color_cycle[2]
+# end
+RM2_0_538D_RE_D_0_9E6 = DelimitedFiles.readdlm("$(path)/RM2_0.538D_RE_D_0.9E6.csv", ',',Float64)
+RM2_0_538D_RE_D_1_3E6 = DelimitedFiles.readdlm("$(path)/RM2_0.538D_RE_D_1.3E6.csv", ',',Float64)
+# PyPlot.plot(RM2_0_538D_RE_D_0_9E6[:,1],RM2_0_538D_RE_D_0_9E6[:,2],"k--",label="Exp. 0.9e6 RE_d")
+PyPlot.plot(RM2_0_538D_RE_D_1_3E6[:,1],RM2_0_538D_RE_D_1_3E6[:,2],"k-",label="Exp. 1.2e6 RE_d")
+# PyPlot.plot(right_TSR,right_CP,"ko",label="Right Only Exp.")
+PyPlot.legend()
+PyPlot.xlabel("TSR")
+PyPlot.ylabel("Cp")
+
+PyPlot.figure("Rp")
+PyPlot.plot((1:length(RpSteady[1,15,:,7]))./length(RpSteady[1,15,:,7]).*360,RpSteady[1,15,:,7],".-",label="No Added Mass")
+PyPlot.legend()
+PyPlot.ylabel("Rp")
+PyPlot.xlabel("Azimuth")
+
+PyPlot.figure("Tp")
+PyPlot.plot((1:length(TpSteady[1,15,:,7]))./length(TpSteady[1,15,:,7]).*360,TpSteady[1,15,:,7],".-",label="No Added Mass")
+PyPlot.legend()
+PyPlot.ylabel("Tp")
+PyPlot.xlabel("Azimuth")
+
+PyPlot.figure("Alpha")
+PyPlot.plot((1:length(alphaSteady[1,15,:,7]))./length(alphaSteady[1,15,:,7]).*360,alphaSteady[1,15,:,7]./2.0./pi.*360,".-",label="Added Mass")
+PyPlot.legend()
+PyPlot.ylabel("Alpha")
+PyPlot.xlabel("Azimuth")
+
+

examples/RM2/airfoils/Airfoils copy.txt

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+04/10/97
+
+Coordinates for the SNL airfoils:
+
+	SNL 0015/47	SNL 0018/50	SNL 0021/50
+	X	(Y	X	(Y	X	(Y
+0.00000	0.00000	0.00000	0.00000	0.00000	0.00000
+0.00020	0.00166	0.00337	0.00646	0.00343	0.00790
+0.00508	0.01091	0.01274	0.01431	0.01291	0.01728
+0.01507	0.02060	0.02713	0.02282	0.02740	0.02735
+0.02872	0.02867	0.04621	0.03160	0.04653	0.03771
+0.04729	0.03615	0.06970	0.04042	0.07001	0.04806
+0.07062	0.04329	0.09730	0.04903	0.09753	0.05814
+0.09832	0.05006	0.12870	0.05726	0.12878	0.06772
+0.13002	0.05630	0.16353	0.06491	0.16339	0.07660
+0.16533	0.06192	0.20142	0.07183	0.20098	0.08460
+0.20386	0.06678	0.24193	0.07786	0.24113	0.09152
+0.24517	0.07080	0.28464	0.08283	0.28339	0.09721
+0.28880	0.07383	0.32907	0.08663	0.32730	0.10149
+0.33426	0.07575	0.37471	0.08908	0.37235	0.10417
+0.38104	0.07643	0.42107	0.09000	0.41805	0.10507
+0.42860	0.07556	0.46759	0.08902	0.46384	0.10379
+0.47688	0.07272	0.51422	0.08561	0.50965	0.09968
+0.52610	0.06808	0.56140	0.07982	0.55603	0.09272
+0.57603	0.06216	0.60914	0.07234	0.60311	0.08368
+0.62618	0.05535	0.65698	0.06379	0.65048	0.07323
+0.67600	0.04801	0.70440	0.05462	0.69767	0.06193
+0.72489	0.04046	0.75083	0.04535	0.74412	0.05037
+0.77244	0.03306	0.79560	0.03642	0.78921	0.03911
+0.81734	0.02608	0.83798	0.02827	0.83220	0.02869
+0.85951	0.01979	0.87718	0.02125	0.87224	0.01959
+0.89801	0.01441	0.91233	0.01562	0.90843	0.01217
+0.93212	0.01005	0.94258	0.01150	0.93980	0.00663
+0.96114	0.00676	0.96711	0.00881	0.96541	0.00296
+0.98447	0.00448	0.98519	0.00740	0.98439	0.00095
+0.99685	0.00349	0.99627	0.00687	0.99606	0.00015
+1.00000	0.00000	1.00000	0.00678	1.00000	0.00000
+
+The 18/50 was thickened up near the trailing edge so we could actually build it (we can't make a razor-edged extrusion).  Although we had to do a similar thing with the other two airfoils when we built models, I don't have those coordinates available.

examples/RM2/airfoils/Airfoils.txt

@@ -0,0 +1,39 @@
+04/10/97
+
+Coordinates for the SNL airfoils:
+
+	SNL 0015/47	SNL 0018/50	SNL 0021/50
+	X	(Y	X	(Y	X	(Y
+0.00000	0.00000	0.00000	0.00000	0.00000	0.00000
+0.00020	0.00166	0.00337	0.00646	0.00343	0.00790
+0.00508	0.01091	0.01274	0.01431	0.01291	0.01728
+0.01507	0.02060	0.02713	0.02282	0.02740	0.02735
+0.02872	0.02867	0.04621	0.03160	0.04653	0.03771
+0.04729	0.03615	0.06970	0.04042	0.07001	0.04806
+0.07062	0.04329	0.09730	0.04903	0.09753	0.05814
+0.09832	0.05006	0.12870	0.05726	0.12878	0.06772
+0.13002	0.05630	0.16353	0.06491	0.16339	0.07660
+0.16533	0.06192	0.20142	0.07183	0.20098	0.08460
+0.20386	0.06678	0.24193	0.07786	0.24113	0.09152
+0.24517	0.07080	0.28464	0.08283	0.28339	0.09721
+0.28880	0.07383	0.32907	0.08663	0.32730	0.10149
+0.33426	0.07575	0.37471	0.08908	0.37235	0.10417
+0.38104	0.07643	0.42107	0.09000	0.41805	0.10507
+0.42860	0.07556	0.46759	0.08902	0.46384	0.10379
+0.47688	0.07272	0.51422	0.08561	0.50965	0.09968
+0.52610	0.06808	0.56140	0.07982	0.55603	0.09272
+0.57603	0.06216	0.60914	0.07234	0.60311	0.08368
+0.62618	0.05535	0.65698	0.06379	0.65048	0.07323
+0.67600	0.04801	0.70440	0.05462	0.69767	0.06193
+0.72489	0.04046	0.75083	0.04535	0.74412	0.05037
+0.77244	0.03306	0.79560	0.03642	0.78921	0.03911
+0.81734	0.02608	0.83798	0.02827	0.83220	0.02869
+0.85951	0.01979	0.87718	0.02125	0.87224	0.01959
+0.89801	0.01441	0.91233	0.01562	0.90843	0.01217
+0.93212	0.01005	0.94258	0.01150	0.93980	0.00663
+0.96114	0.00676	0.96711	0.00881	0.96541	0.00296
+0.98447	0.00448	0.98519	0.00740	0.98439	0.00095
+0.99685	0.00349	0.99627	0.00687	0.99606	0.00015
+1.00000	0.00000	1.00000	0.00678	1.00000	0.00000
+
+The 18/50 was thickened up near the trailing edge so we could actually build it (we can't make a razor-edged extrusion).  Although we had to do a similar thing with the other two airfoils when we built models, I don't have those coordinates available.

examples/RM2/airfoils/NACA_0012 copy.dat

@@ -0,0 +1,130 @@
+NACA 0012
+Sheldahl, R. E. and Klimas, P. C., Aerodynamic Characteristics of Seven Airfoil Sections Through 180 Degrees Angle of Attack for Use in Aerodynamic Analysis of Vertical Axis Wind Turbines,
+SAND80-2114, March 1981, Sandia National Laboratories, Albuquerque, New Mexico.
+1        Number of airfoil tables in this file
+3.6     Reynolds numbers in millions
+0.0      Control setting
+0.0     Stall angle (deg)
+0.0   Zero Cn angle of attack (deg)
+0.0   Cn slope for zero lift (dimensionless)
+0.0   Cn extrapolated to value at positive stall angle of attack
+0.0   Cn at stall value for negative angle of attack
+0.0   Angle of attack for minimum CD (deg)
+0.0   Minimum CD value
+-180.0000 -0.0000 .0250
+-175.0000 .6900 .0550
+-170.0000 .8500 .1400
+-165.0000 .6750 .2300
+-160.0000 .6600 .3200
+-155.0000 .7400 .4200
+-150.0000 .8500 .5750
+-145.0000 .9100 .7550
+-140.0000 .9450 .9250
+-135.0000 .9450 1.0850
+-130.0000 .9100 1.2250
+-125.0000 .8400 1.3500
+-120.0000 .7350 1.4650
+-115.0000 .6250 1.5550
+-110.0000 .5100 1.6350
+-105.000 .3700 1.7000
+-100.000 .22 1.7500
+-95.0000 .0700 1.7800
+-90.0000 -.0700 1.8000
+-85.000 -.2200 1.8000
+-80.0000 -.3700 1.7800
+-75.0000 -.5150 1.7350
+-70.0000 -0.6500 1.6650
+-65.0000 -.7650 1.5750
+-60.000 -.8750 1.4700
+-55.00000 -.9650 1.3450
+-50.0000 -1.0400 1.2150
+-45.0000 -1.0850 1.0750
+-40.0000 -1.0750 .9200
+-35.0000 -1.0200 .7450
+-30.0000 -.9150 .5700
+-27.0000 -.9846 .4730
+-26.0000 -.9313 .4460
+-25.0000 -.8780 .4200
+-24.0000 -.8246 .3940
+-23.0000 -.7715 .3690
+-22.0000 -.7179 .3440
+-21.0000 -.6643 .3200
+-20.0000 -.6120 .2970
+-19.0000 -.5591 .2740
+-18.0000 -.5047 .2520
+-17.0000 -.4455 .2310
+-15.0000 -.3792 .2100
+-15.0000 -.3306 .1900
+-14.0000 -.2893 .1060
+-13.0000 -.2759 .0222
+-12.0000 -.4832 .0217
+-11.0000 -.9132 .0204
+-10.0000 -.9811 .0184
+-9.0000 -.9352 .0167
+-8.00000 -.8542 .0153
+-7.0000 -.7700 .0135
+-6.0000 -.6600 .0125
+-5.0000 -.5500 .0113
+-4.0000 -.4400 .0098
+-3.00000 -.3300 .0089
+-2.0000 -.2200 .0084
+-1.0000 -.1100 .0080
+0.0000 0.0000 .0079
+1.0000 .1100 .0080
+2.0000 .2200 .0084
+3.00000 .3300 .0089
+4.0000 .4400 .0098
+5.0000 .5500 .0113
+6.0000 .6600 .0125
+7.0000 .7700 .0135
+8.00000 .8542 .0153
+9.0000 .9352 .0167
+10.0000 .9811 .0184
+11.0000 .9132 .0204
+12.0000 .4832 .0217
+13.0000 .2759 .0222
+14.0000 .2893 .1060
+15.0000 .3306 .1900
+15.0000 .3792 .2100
+17.0000 .4455 .2310
+18.0000 .5047 .2520
+19.0000 .5591 .2740
+20.0000 .6120 .2970
+21.0000 .6643 .3200
+22.0000 .7179 .3440
+23.0000 .7715 .3690
+24.0000 .8246 .3940
+25.0000 .8780 .4200
+26.0000 .9313 .4460
+27.0000 .9846 .4730
+30.0000 .9150 .5700
+35.0000 1.0200 .7450
+40.0000 1.0750 .9200
+45.0000 1.0850 1.0750
+50.0000 1.0400 1.2150
+55.00000 .9650 1.3450
+60.000 .8750 1.4700
+65.0000 .7650 1.5750
+70.0000 0.6500 1.6650
+75.0000 .5150 1.7350
+80.0000 .3700 1.7800
+85.000 .2200 1.8000
+90.0000 .0700 1.8000
+95.0000 -.0700 1.7800
+100.000 -.22 1.7500
+105.000 -.3700 1.7000
+110.0000 -.5100 1.6350
+115.0000 -.6250 1.5550
+120.0000 -.7350 1.4650
+125.0000 -.8400 1.3500
+130.0000 -.9100 1.2250
+135.0000 -.9450 1.0850
+140.0000 -.9450 .9250
+145.0000 -.9100 .7550
+150.0000 -.8500 .5750
+155.0000 -.7400 .4200
+160.0000 -.6600 .3200
+165.0000 -.6750 .2300
+170.0000 -.8500 .1400
+175.0000 -.6900 .0550
+180.0000 0.0000 .0250