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Minor output fixes and output testing (#14)
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Original file line number | Diff line number | Diff line change |
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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 | ||
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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 | ||
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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) | ||
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Rfuse = 2.0 m ( 6.4 ft) | ||
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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 | ||
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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) |
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Original file line number | Diff line number | Diff line change |
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@testset "outputs" verbose=true begin | ||
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ac = load_default_model() | ||
size_aircraft!(ac; printiter=false); | ||
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@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") | ||
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f = open(io->TASOPT.aero(ac,io=io), "temp.txt", "w") | ||
@test read("aero.txt", String) == read("temp.txt", String) | ||
rm("temp.txt") | ||
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f = open(io->TASOPT.geometry(ac,io=io), "temp.txt", "w") | ||
@test read("geom.txt", String) == read("temp.txt", String) | ||
rm("temp.txt") | ||
end | ||
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@testset "output plots" begin | ||
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TASOPT.stickfig(ac) | ||
@test 1 == 1 | ||
TASOPT.high_res_airplane_plot(ac) | ||
@test 2 == 2 | ||
TASOPT.plot_details(ac) | ||
@test 3 == 3 | ||
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end | ||
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end |
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Original file line number | Diff line number | Diff line change |
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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) | ||
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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) | ||
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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) | ||
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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) | ||
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Wftnkins = 0.0 N ( 0.0 lb) | ||
Wftank = 0.0 N ( 0.0 lb) | ||
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lftank = 0.0 m ( 0.0 ft) | ||
Rftank = 0.0 m ( 0.0 ft) | ||
ηtank = 100.0 % | ||
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