add some notes in the boundary layer for later, move dfdc polar fitti…

…ng code here for now

src/C4Blade/dfdc_polar_fitting.jl

@@ -0,0 +1,125 @@
+project_dir = dirname(dirname(@__FILE__))
+if project_dir == ""
+    project_dir = "."
+end
+
+# TODO: change datapath to test directory or validation data directory
+datapath = project_dir * "/validation/data/"
+savepath = project_dir * "/validation/data/"
+# savepath = project_dir * "/dfdc_airfoil_approximations/"
+afname = "dfdc_naca4412"
+
+using LsqFit
+using FLOWMath
+const fm = FLOWMath
+using Plots
+using DuctAPE.C4Blade
+const c4b = C4Blade
+
+function linfit(aoas, cl0, dclda)
+    return dclda .* aoas .+ cl0
+end
+
+function quadfit(cls, cdmin, clcdmin, dcddcl2)
+    return dcddcl2 * (cls .- clcdmin) .^ 2 .+ cdmin
+end
+
+# - Read in Polar - #
+info, Re_ref, mach, aoa, cl, cd = c4b.parsefile(datapath * "naca4412.dat", true)
+clsp = fm.Akima(aoa, cl)
+cdsp = fm.Akima(aoa, cd)
+
+# - Plot Polar - #
+plot(aoa * 180 / pi, cl)
+
+# - Chop Polar Down for Fits and replot - #
+aoachop = range(-5, 10, 100) * pi / 180
+clchop = clsp(aoachop)
+cdchop = cdsp(aoachop)
+pcl = plot(aoachop, clchop)
+pcd = plot(cdchop, clchop)
+
+# - Get cdmin and cl at cdmin as well as zero lift angle of attack- #
+cdmin, cdminid = findmin(cdchop)
+clcdmin = clchop[cdminid]
+
+_, zeroclid = findmin(abs.(clchop))
+alpha0 = fm.linear(
+    [clchop[zeroclid - 1], clchop[zeroclid]],
+    [aoachop[zeroclid - 1], aoachop[zeroclid]],
+    0.0,
+)
+
+_, zeroalphaid = findmin(abs.(aoachop))
+cl0 = fm.linear(
+    [aoachop[zeroalphaid - 1], aoachop[zeroalphaid]],
+    [clchop[zeroalphaid - 1], clchop[zeroalphaid]],
+    0.0,
+)
+
+# - Fit drag curve - #
+p0 = [0.05]
+quadfitwrap(cls, p) = quadfit(clchop, cdmin, clcdmin, p[1])
+cdfit = LsqFit.curve_fit(quadfitwrap, clchop, cdchop, p0)
+
+dcddcl2 = cdfit.param[1]
+
+# - Plot fitted curve - #
+plot!(pcd, quadfit(clchop, cdmin, clcdmin, cdfit.param[1]), clchop)
+
+# - Fit Lift Curve - #
+p0 = [2.0 * pi]
+linfitwrap(aoas, p) = linfit(aoas, cl0, p[1])
+clfit = LsqFit.curve_fit(linfitwrap, aoachop, clchop, p0)
+
+dclda = clfit.param[1]
+
+# - Plot fitted curve - #
+plot!(pcl, aoachop, linfit(aoachop, cl0, clfit.param[1]))
+
+# - Select clmin, clmax - #
+clmin, clminid = findmin(clchop)
+clmaxid = findlast(x -> x < 0.1, clfit.resid)
+clmax = clchop[clmaxid]
+
+# - Manually set various paramters - #
+Re_exp = -0.5
+mcrit = 0.7
+cmcon = 0.0
+dclda_stall = 0.1
+dcl_stall = 0.1
+
+# - `alpha0::Float` : zero lift angle of attack
+# - `clmax::Float` : maximum cl
+# - `clmin::Float` : minimum cl
+# - `dclda::Float` : lift curve slope (1/radians)
+# - `dclda_stall::Float` :  lift curve slope post-stall (1/radians)
+# - `dcl_stall::Float` : cl increment from initial to total stall.
+# - `cdmin::Float` : minimum cd
+# - `cldmin::Float` : cl at cdmin
+# - `dcdcl2::Float` : quadratic curve factor for cd curve (d(cd)/d(cl^2))
+# - `cmcon::Float` : pitching moment constant
+# - `Re_ref::Float` : reference Reynolds number at which cd values apply
+# - `Re_exp::Float` : Reynolds number exponent scaling (cd = cd*(Re/Re_ref)^Re_exp)
+# - `mcrit::Float` : critical Mach number
+
+f = open(savepath * afname * ".jl", "w")
+
+write(
+    f,
+    "alpha0      = $alpha0
+    clmax       = $clmax
+    clmin       = $clmin
+    dclda       = $dclda
+    dclda_stall = $dclda_stall
+    dcl_stall   = $dcl_stall
+    cdmin       = $cdmin
+    clcdmin     = $clcdmin
+    dcddcl2     = $dcddcl2
+    cmcon       = $cmcon
+    Re_ref      = $Re_ref
+    Re_exp      = $Re_exp
+    mcrit       = $mcrit",
+)
+
+close(f)

src/postprocess/postprocess.jl

@@ -180,10 +180,10 @@ function post_process(
     # - Extract PrePost Cache - #
     reset_containers!(prepost_containers; exception_keys=(:panels, :ivb))
     (;
-        # stuff from pre-process
+        # Stuff from Pre-process
         panels,
         ivb,
-        # rotor stuff
+        # Rotor Stuff
         rotor_inviscid_thrust,
         rotor_inviscid_thrust_dist,
         rotor_viscous_thrust,
@@ -207,14 +207,13 @@ function post_process(
         blade_normal_force_per_unit_span,
         blade_tangential_force_per_unit_span,
         blade_loading_intermediate_containers,
-        # body stuff
+        # Body Stuff
         zpts,
         vtan_tuple,
         cp_tuple,
         body_thrust,
         body_force_coefficient,
-        # cp_tuple,
-        # totals stuff
+        # Totals Stuff
         total_thrust,
         total_torque,
         total_power,
@@ -223,6 +222,9 @@ function post_process(
         total_CT,
         total_CQ,
         total_CP,
+        # Boundary Layer Stuff #TODO: add these to caches at some point (requires re-work of boundary layer implementation likey)
+        # duct_viscous_drag,
+        # boundary_layer_outputs,
     ) = prepost_containers
 
     # - Extract Panels - #
@@ -505,6 +507,8 @@ function post_process(
 
     if boundary_layer_options.model_drag
 
+        #TODO; make this in place
+        # compute_viscous_drag_duct!(duct_viscous_drag, boundary_layer_outputs,
         duct_viscous_drag, boundary_layer_outputs = compute_viscous_drag_duct(
             boundary_layer_options,
             Vtan_out[1:Int(body_vortex_panels.npanel[1])],