Minor output fixes and output testing (#14)

Project.toml

@@ -7,6 +7,7 @@ version = "1.0.0-DEV"
 BenchmarkTools = "6e4b80f9-dd63-53aa-95a3-0cdb28fa8baf"
 Dates = "ade2ca70-3891-5945-98fb-dc099432e06a"
 Dierckx = "39dd38d3-220a-591b-8e3c-4c3a8c710a94"
+DocStringExtensions = "ffbed154-4ef7-542d-bbb7-c09d3a79fcae"
 ForwardDiff = "f6369f11-7733-5829-9624-2563aa707210"
 LinearAlgebra = "37e2e46d-f89d-539d-b4ee-838fcccc9c8e"
 NLopt = "76087f3c-5699-56af-9a33-bf431cd00edd"

src/IO/outputs.jl

@@ -1473,7 +1473,6 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
             ax.plot( [xi.+lnace/2, xi.+1.0] , -1.0 .* [yi, yi], color = "k", lw = 2, zorder = wingz-2)
 
 
-
         # Plot NP and CG range
             ax.scatter(parg[igxNP], 0.0, color = "k", marker="o", zorder = 21, label = "NP")
             ax.text(parg[igxNP], -1.0, "NP", fontsize=label_fs-2.0, ha="center", va="center", zorder = 21)
@@ -1498,7 +1497,6 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
     #  ax.plot([parg[igxftank]-l/2, parg[igxftank]+l/2],[0.0, 0.0], zorder = 21)
 
 
-
     # Annotations
     ax.text(0, 16, @sprintf("PFEI = %5.3f J/Nm\nM\$_{cruise}\$ = %.2f\nWMTO = %.1f tonnes\nSpan = %5.1f m\nco    = %5.1f m\n\$ \\Lambda \$ = %.1f\$^\\circ\$\nRfuse = %5.1f m\nL/D = %3.2f",
      parm[imPFEI], para[iaMach, ipcruise1],parg[igWMTO]/9.81/1000, parg[igb], parg[igco], parg[igsweep], parg[igRfuse], para[iaCL, ipcruise1]/para[iaCD, ipcruise1]),
@@ -1559,8 +1557,6 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
 
     # Scale bar
 
-
-
     return ax
 end
 

test/aero.txt

@@ -0,0 +1,27 @@
+Aerodynamics:
+ -------------- 
+Ref.Area= 139.48268 m²
+L/D     = 17.60833
+CL      = 0.57000
+CD      = 0.03237
+CDfuse  = 0.00681
+CDi     = 0.01116
+CDwing  = 0.00820
+CDhtail = 0.00259
+CDvtail = 0.00175
+CDnace  = 0.00186
+CDBLIf  = -0.00000
+CDBLIw  = -0.00000
+
+Drag Areas = CD × Sref:
+CL     × Sref = 79.50513 m²
+CD     × Sref = 4.51520 m²
+CDfuse × Sref = 0.95001 m²
+CDi    × Sref = 1.55662 m²
+CDwing × Sref = 1.14362 m²
+CDhtail× Sref = 0.36162 m²
+CDvtail× Sref = 0.24445 m²
+CDnace × Sref = 0.25888 m²
+CDBLIf × Sref = -0.00000 m²
+CDBLIw × Sref = -0.00000 m²
+

test/geom.txt

@@ -0,0 +1,44 @@
+Fuselage Layout:
+ -------------- 
+xnose   =   0.0 m (     0.0 ft)
+xend    =  37.8 m (   124.0 ft)
+xwing   =  18.8 m (    61.7 ft)
+xhtail  =  36.2 m (   118.9 ft)
+xvtail  =  35.1 m (   115.0 ft)
+xblend1 =   6.1 m (    20.0 ft)
+xblend2 =  29.6 m (    97.0 ft)
+xshell1 =   5.2 m (    17.0 ft)
+xshell2 =  31.1 m (   102.0 ft)
+xhbend  =  31.0 m (   101.7 ft)
+xvbend  =  31.2 m (   102.3 ft)
+xwbox   =  16.0 m (    52.6 ft)
+xhbox   =  34.9 m (   114.5 ft)
+xvbox   =  33.5 m (   110.0 ft)
+xtshaft =   0.0 m (     0.0 ft)
+xgen    =   0.0 m (     0.0 ft)
+xcat    =   0.0 m (     0.0 ft)
+xftank  =   0.0 m (     0.0 ft)
+
+Rfuse  =   2.0 m (     6.4 ft)
+
+Stability:
+ -------------- 
+xNP     =  19.9 m (    65.3 ft)
+xCGfwd  =  17.6 m (    57.8 ft)
+xCGaft  =  19.6 m (    64.4 ft)
+xSMfwd  = 0.5416
+xSMaft  = 0.0637
+
+Wing Layout:
+ -------------- 
+AR      = 10.100 
+sweep   = 26.000 
+lambdas = 0.700 
+lambdat = 0.250 
+co      =   6.2 m (    20.4 ft)
+cs      =   4.4 m (    14.3 ft)
+ct      =   1.6 m (     5.1 ft)
+bo      =   3.6 m (    11.8 ft)
+bs      =  10.7 m (    35.1 ft)
+b       =  37.5 m (   123.1 ft)
+S       = 139.5 m²(  1501.4 ft²)

test/runtests.jl

@@ -4,5 +4,8 @@ using Test
 @testset verbose=true "TASOPT" begin
     include("unit_test_structures.jl")
     include("unit_test_aero.jl")
+    include("unit_test_heat_exchanger.jl")
     include("regression_test_wsize.jl")
+    include("unit_test_outputs.jl")
+
 end

test/unit_test_heat_exchanger.jl

@@ -5,9 +5,6 @@
 #     exchanger in air. It assumes that air in flowing through the exchanger
 #     and heat is absorbed by a coolant fluid.
 
-using TASOPT
-using Test
-
 #---------------------------------     
 # Test functions individually
 #---------------------------------

test/unit_test_outputs.jl

@@ -0,0 +1,32 @@
+
+@testset "outputs" verbose=true begin
+
+    ac = load_default_model()
+    size_aircraft!(ac; printiter=false);
+
+    @testset "output summaries" begin
+        f = open(io->TASOPT.weight_buildup(ac,io=io), "temp.txt", "w")
+        @test read("weights.txt", String) == read("temp.txt", String)
+        rm("temp.txt")
+
+        f = open(io->TASOPT.aero(ac,io=io), "temp.txt", "w")
+        @test read("aero.txt", String) == read("temp.txt", String)
+        rm("temp.txt")
+
+        f = open(io->TASOPT.geometry(ac,io=io), "temp.txt", "w")
+        @test read("geom.txt", String) == read("temp.txt", String)
+        rm("temp.txt")
+    end
+
+    @testset "output plots" begin
+
+        TASOPT.stickfig(ac)
+        @test 1 == 1
+        TASOPT.high_res_airplane_plot(ac)
+        @test 2 == 2
+        TASOPT.plot_details(ac)
+        @test 3 == 3
+
+    end
+
+end

test/weights.txt

@@ -0,0 +1,52 @@
+Weight build-up:
+ -------------- 
+Wempty  +   466014.1 N (104764.1 lb)
+Wpay    +   172146.2 N ( 38700.0 lb)
+Wfuel   +   233069.6 N ( 52396.1 lb)
+--------------------
+WMTO    =   871229.9 N (195860.3 lb)
+
+Wfuse   +   195735.6 N ( 44003.1 lb)
+Wwing   +   128764.2 N ( 28947.3 lb)
+Wvtail  +     9899.4 N (  2225.5 lb)
+Whtail  +    14759.3 N (  3318.0 lb)
+Wtesys  +        0.0 N (     0.0 lb)
+Wftank  +        0.0 N (     0.0 lb)
+Wadd    +    56629.9 N ( 12730.9 lb)
+--------------------
+Wempty  =   405788.5 N ( 91224.9 lb)
+
+Wcap    +    74931.7 N ( 16845.3 lb)
+Wweb    +     3583.1 N (   805.5 lb)
+Wflap   +    15703.0 N (  3530.2 lb)
+Wslat   +     7851.5 N (  1765.1 lb)
+Waile   +     3140.6 N (   706.0 lb)
+Wlete   +     7851.5 N (  1765.1 lb)
+Wribs   +    11777.2 N (  2647.6 lb)
+Wspoi   +     1570.3 N (   353.0 lb)
+Wwatt   +     2355.4 N (   529.5 lb)
+--------------------
+Wwing  =   128764.2 N ( 28947.3 lb)
+
+Wtshaft +        0.0 N (     0.0 lb) × 2
+Wcat    +        0.0 N (     0.0 lb) × 2
+Waftfan +        0.0 N (     0.0 lb) × 2
+WaftGB  +        0.0 N (     0.0 lb) × 2
+Wgen    +        0.0 N (     0.0 lb) × 4
+Wrect   +        0.0 N (     0.0 lb) × 4
+Wcables +        0.0 N (     0.0 lb) ----
+Winv    +        0.0 N (     0.0 lb) × 6
+Wmot    +        0.0 N (     0.0 lb) × 6
+Wfan    +        0.0 N (     0.0 lb) × 6
+WfanGB  +        0.0 N (     0.0 lb) × 6
+Wtms    +        0.0 N (     0.0 lb) ----
+--------------------
+Wtesys  =        0.0 N (     0.0 lb)
+
+Wftnkins  =        0.0 N (     0.0 lb)
+Wftank    =        0.0 N (     0.0 lb)
+
+lftank    =        0.0 m (     0.0 ft)
+Rftank    =        0.0 m (     0.0 ft)
+ηtank     = 100.0 % 
+