Merge pull request #57 from askprash/dev_fuse_remodel

Refactoring the fuselage sizing.

Some of the other PR's may have to be updated to use the new fuselage layouts.
More unit tests, documentation and plotting tools coming in the next PR...

.gitignore

@@ -20,3 +20,4 @@ docs/build/*
 .VSCodeCounter/*
 .vscode/*
 .CondaPkg/*
+__pycache__/*

docs/src/aero/drag.md

@@ -48,7 +48,7 @@ aerodynamics.blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr)
 aerodynamics.blvar(simi,lami,wake, Reyn,Mach, fexcr,
                       x, θ ,δs ,ue )
 
-aerodynamics.fusebl!(pari, parg, para, parm, ip)
+aerodynamics.fusebl!(fuse, parm, para, ip)
 ```
 
 ---

docs/src/sizing/sizing.md

@@ -17,11 +17,11 @@ TASOPT.woper(ac, itermax)
 A sized aircraft's mission performance can be obtained (`mission!`), along with operation constraints via a pitch trim calculation (`balance`) and balanced field length calculation (`takeoff!`).
 
 ```@docs
-TASOPT.mission!(pari, parg, parm, para, pare, Ldebug)
+TASOPT.mission!(pari, parg, parm, para, pare, fuse, Ldebug)
 
 TASOPT.takeoff!(ac; printTO)
 
-TASOPT.balance(pari, parg, para, rfuel, rpay, ξpay, itrim)
+TASOPT.balance(pari, parg, para, fuse, rfuel, rpay, ξpay, itrim)
 
 ```
 

docs/src/structures/fuselage.md

@@ -339,5 +339,5 @@ x \hspace{-0.45ex} W_{\rm vbend}
 \end{aligned}$$
 
 ```@docs
-TASOPT.fusew
+TASOPT.fusew!
 ```

example/example_opt.jl

@@ -97,7 +97,7 @@ function obj(x, grad)
     # f = f + penfac*max(0.0, constraint)^2
 
     # # Ensure fans will fit within fuselage
-    # daftfanmax = min(3.0, 0.9*ac.parg[igRfuse])
+    # daftfanmax = min(3.0, 0.9*ac.fuselage.layout.radius)
     # daftfan = ac.parg[igdaftfan]
     # constraint = daftfan/daftfanmax - 1.0
     # penfac = ac.parg[igWpay]

example/example_regional.toml

@@ -103,7 +103,7 @@
     dRadius = "13.0 in"      # Downward shift of lower bubbles
     y_offset = 0.0         # y offset of bubble center
     floor_depth = "6.0 in" # depth of floor beams
-    Nwebs = 1              # number of webs (for double bubble designs)
+    Nwebs = 0              # number of webs (for double bubble designs)
 
     a_nose = 1.7 # Nose radius = Rfuse*(1 - xi^a_nose)^(1/a_nose)
     b_tail = 1.75 # Tail radius = Rfuse*(1 - xi^b_tail)

example/example_widebody.toml

@@ -105,7 +105,7 @@
     dRadius = "0 in"      # Downward shift of lower bubbles
     y_offset = 0.0         # y offset of bubble center
     floor_depth = "8.0 in" # depth of floor beams
-    Nwebs = 1              # number of webs (for double bubble designs)
+    Nwebs = 0              # number of webs (for double bubble designs)
 
     a_nose = 1.65 # Nose radius = Rfuse*(1 - xi^a_nose)^(1/a_nose)
     b_tail = 2.0 # Tail radius = Rfuse*(1 - xi^b_tail)

src/IO/default_input.toml

@@ -139,12 +139,11 @@
     cabin_pressure_altitude = "8000.0 ft"
 
 [Fuselage.Geometry]
+    number_of_bubbles = 1  # SingleBubble or MultiBubble Designs
     radius = "77 in"       # Fuselage radius
     dRadius = "15 in"      # Downward shift of lower bubbles
     y_offset = 0.0         # y offset of bubble center
     floor_depth = "5.0 in" # depth of floor beams
-    Nwebs = 1              # number of webs (for double bubble designs)
-
     a_nose = 1.65 # Nose radius = Rfuse*(1 - xi^a_nose)^(1/a_nose)
     b_tail = 2.0 # Tail radius = Rfuse*(1 - xi^b_tail)
     tailcone_taper = 0.3
@@ -373,8 +372,24 @@
 
     # Allowable stresses at sizing cases:
     ## Fuselage pressurization skin stress and bending skin+stringer stress
-    sigma_fuse_skin = "15e3 lbf/in2" 
-    sigma_fuse_bending = "30e3 lbf/in2"
+    skin_material = "TASOPT-Al"
+    skin_max_avg_stress = 1.1
+    skin_safety_factor = 3.0
+    # the sigma_max works out to be roughly 15e3 lbf/in2
+
+    bending_material = "TASOPT-Al"
+    bending_max_avg_stress = 1.1
+    bending_safety_factor = 1.5
+    # the sigma_max works out to be roughly 30e3 lbf/in2
+
+    cone_material = "TASOPT-Al"
+    cone_max_avg_stress = 1.1
+    cone_safety_factor = 2.0
+
+    floor_material = "TASOPT-Al"
+    floor_max_avg_stress = 1.1
+    floor_safety_factor = 1.5
+
     ## Wing and tail bending and shear stresses
     sigma_caps    = "30e3 lbf/in2"
     sigma_struts  = "30e3 lbf/in2"
@@ -386,8 +401,6 @@
     E_struts        = "10e6 lbf/in2"
 
     # Material densities (Aluminium)
-    skin_density = 2700.0
-    fuse_stringer_density = 2700.0
     wing_tail_cap_density = 2700.0
     wing_tail_web_density = 2700.0
     strut_density = 2700.0

src/IO/output_csv.jl

@@ -225,9 +225,9 @@ Example usage:
 default_output_indices = 
     Dict("pari" => Colon(),
         "parg" => [#weights
-                    igWMTO, igWfuel, igWpay, igWpaymax, igfhpesys, igflgnose,igflgmain,
+                    igWMTO, igWfuel, igWpay, igWpaymax, igflgnose,igflgmain,
                     igWweb,igWcap, igfflap,igfslat, igfaile, igflete, igfribs, igfspoi, igfwatt,
-                    igWfuse, igWwing, igWvtail, igWhtail, igWtesys, igWftank, 
+                 igWwing, igWvtail, igWhtail, igWtesys, igWftank, 
 
                     #other
                     igdfan, igGearf,

src/IO/outputs.jl

@@ -5,8 +5,9 @@ using PythonCall
 function weight_buildup(ac::aircraft; io=stdout)
     parg = ac.parg
     pari = ac.pari
+    fuselage = ac.fuselage
     Wempty  = parg[igWMTO] - parg[igWfuel] - parg[igWpay]
-    Whpesys = parg[igWMTO] * parg[igfhpesys]
+    Whpesys = parg[igWMTO] * fuselage.HPE_sys.W
     Wlgnose = parg[igWMTO] * parg[igflgnose]
     Wlgmain = parg[igWMTO] * parg[igflgmain]
     Wtotadd = Whpesys + Wlgnose + Wlgmain
@@ -30,7 +31,7 @@ function weight_buildup(ac::aircraft; io=stdout)
     printstyled(io, @sprintf("WMTO    = %10.1f N (%8.1f lb)\n\n",
                          parg[igWMTO], parg[igWMTO]/lbf_to_N); color=:bold)
 
-    @printf(io,"Wfuse   + %10.1f N (%8.1f lb)\n", parg[igWfuse ], parg[igWfuse ]/lbf_to_N)
+    @printf(io,"Wfuse   + %10.1f N (%8.1f lb)\n", fuselage.weight, fuselage.weight/lbf_to_N)
     @printf(io,"Wwing   + %10.1f N (%8.1f lb)\n", parg[igWwing ], parg[igWwing ]/lbf_to_N)
     @printf(io,"Wvtail  + %10.1f N (%8.1f lb)\n", parg[igWvtail], parg[igWvtail]/lbf_to_N)
     @printf(io,"Whtail  + %10.1f N (%8.1f lb)\n", parg[igWhtail], parg[igWhtail]/lbf_to_N)
@@ -39,9 +40,9 @@ function weight_buildup(ac::aircraft; io=stdout)
     @printf(io,"Wadd    + %10.1f N (%8.1f lb)\n", Wtotadd, Wtotadd/lbf_to_N)
     @printf(io,"--------------------\n")
     printstyled(io, @sprintf("Wempty  = %10.1f N (%8.1f lb)\n\n", 
-    parg[igWfuse] + parg[igWwing]+ parg[igWvtail] + parg[igWhtail] + 
+    fuselage.weight + parg[igWwing]+ parg[igWvtail] + parg[igWhtail] + 
     parg[igWtesys] + +parg[igWftank] + Wtotadd, 
-    (parg[igWfuse] + parg[igWwing]+ parg[igWvtail] + parg[igWhtail] + 
+    (fuselage.weight + parg[igWwing]+ parg[igWvtail] + parg[igWhtail] + 
     parg[igWtesys] + +parg[igWftank] + Wtotadd)/lbf_to_N); color=:bold)
 
     @printf(io,"Wcap    + %10.1f N (%8.1f lb)\n", parg[igWcap], parg[igWcap]/lbf_to_N)
@@ -122,18 +123,19 @@ end
 """
 function geometry(ac::aircraft; io = stdout)
     parg = ac.parg
+    fuselage = ac.fuselage
     printstyled(io, "Fuselage Layout:\n -------------- \n", color=:bold )
-    @printf(io, "xnose     = %5.1f m (%8.1f ft)\n", parg[igxnose  ] , parg[igxnose   ]/ft_to_m)
-    @printf(io, "xend      = %5.1f m (%8.1f ft)\n", parg[igxend   ] , parg[igxend    ]/ft_to_m)
+    @printf(io, "xnose     = %5.1f m (%8.1f ft)\n", fuselage.layout.x_nose , fuselage.layout.x_nose/ft_to_m)
+    @printf(io, "xend      = %5.1f m (%8.1f ft)\n", fuselage.layout.x_end , fuselage.layout.x_end/ft_to_m)
     @printf(io, "xwing     = %5.1f m (%8.1f ft)\n", parg[igxwing  ] , parg[igxwing   ]/ft_to_m)
     @printf(io, "xhtail    = %5.1f m (%8.1f ft)\n", parg[igxhtail ] , parg[igxhtail  ]/ft_to_m)
     @printf(io, "xvtail    = %5.1f m (%8.1f ft)\n", parg[igxvtail ] , parg[igxvtail  ]/ft_to_m)
-    @printf(io, "xblend1   = %5.1f m (%8.1f ft)\n", parg[igxblend1] , parg[igxblend1 ]/ft_to_m)
-    @printf(io, "xblend2   = %5.1f m (%8.1f ft)\n", parg[igxblend2] , parg[igxblend2 ]/ft_to_m)
-    @printf(io, "xshell1   = %5.1f m (%8.1f ft)\n", parg[igxshell1] , parg[igxshell1 ]/ft_to_m)
-    @printf(io, "xshell2   = %5.1f m (%8.1f ft)\n", parg[igxshell2] , parg[igxshell2 ]/ft_to_m)
-    @printf(io, "xhbend    = %5.1f m (%8.1f ft)\n", parg[igxhbend ] , parg[igxhbend  ]/ft_to_m)
-    @printf(io, "xvbend    = %5.1f m (%8.1f ft)\n", parg[igxvbend ] , parg[igxvbend  ]/ft_to_m)
+    @printf(io, "xblend1   = %5.1f m (%8.1f ft)\n", fuselage.layout.x_start_cylinder , fuselage.layout.x_start_cylinder/ft_to_m)
+    @printf(io, "xblend2   = %5.1f m (%8.1f ft)\n", fuselage.layout.x_end_cylinder , fuselage.layout.x_end_cylinder/ft_to_m)
+    @printf(io, "xshell1   = %5.1f m (%8.1f ft)\n", fuselage.layout.x_pressure_shell_fwd , fuselage.layout.x_pressure_shell_fwd/ft_to_m)
+    @printf(io, "xshell2   = %5.1f m (%8.1f ft)\n", fuselage.layout.x_pressure_shell_aft , fuselage.layout.x_pressure_shell_aft/ft_to_m)
+    @printf(io, "xhbend    = %5.1f m (%8.1f ft)\n", fuselage.bendingmaterial_h.weight.x , fuselage.bendingmaterial_h.weight.x/ft_to_m)
+    @printf(io, "xvbend    = %5.1f m (%8.1f ft)\n", fuselage.bendingmaterial_v.weight.x , fuselage.bendingmaterial_v.weight.x/ft_to_m)
     @printf(io, "xwbox     = %5.1f m (%8.1f ft)\n", parg[igxwbox  ] , parg[igxwbox   ]/ft_to_m)
     @printf(io, "xhbox     = %5.1f m (%8.1f ft)\n", parg[igxhbox  ] , parg[igxhbox   ]/ft_to_m)
     @printf(io, "xvbox     = %5.1f m (%8.1f ft)\n", parg[igxvbox  ] , parg[igxvbox   ]/ft_to_m)
@@ -143,7 +145,7 @@ function geometry(ac::aircraft; io = stdout)
     @printf(io, "xftank    = %5.1f m (%8.1f ft)\n", parg[igxftank ] , parg[igxftank  ]/ft_to_m)
     @printf(io, "xftankaft = %5.1f m (%8.1f ft)\n", parg[igxftankaft ] , parg[igxftankaft  ]/ft_to_m)
 
-    @printf(io, "\nRfuse  = %5.1f m (%8.1f ft)\n", parg[igRfuse ] , parg[igRfuse  ]/ft_to_m)
+    @printf(io, "\nRfuse  = %5.1f m (%8.1f ft)\n", fuselage.layout.cross_section.radius , fuselage.layout.cross_section.radius/ft_to_m)
 
 
     SMfwd = (parg[igxNP] - parg[igxCGfwd])/parg[igcma]
@@ -235,16 +237,17 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
         yw[5] = bs/2.0
         yw[6] = bo/2.0
     # Fuse
-        Rfuse = parg[igRfuse]
-        wfb   = parg[igwfb]
+        fuselage = ac.fuselage
+        Rfuse = fuselage.layout.radius
+        wfb   = fuselage.layout.bubble_center_y_offset
 
-        anose    = parg[iganose]
-        btail    = parg[igbtail]
+        anose    = fuselage.layout.nose_radius
+        btail    = fuselage.layout.tail_radius
 
-        xnose    = parg[igxnose   ]
-        xend     = parg[igxend    ]
-        xblend1  = parg[igxblend1 ]
-        xblend2  = parg[igxblend2 ]
+        xnose    = fuselage.layout.x_nose
+        xend     = fuselage.layout.x_end
+        xblend1  = fuselage.layout.x_start_cylinder
+        xblend2  = fuselage.layout.x_end_cylinder
         xhtail   = parg[igxhtail  ]
         xvtail   = parg[igxvtail  ]
         xwing    = parg[igxwing   ]
@@ -264,7 +267,7 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
         xf = zeros(nnose + ntail + 1)
         yf = zeros(nnose + ntail + 1)
 
-        if pari[iifclose] == 0
+        if fuselage.layout.taper_fuse == 0
             dytail = -hwidth 
         else
             dytail = -0.2*hwidth
@@ -324,7 +327,7 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
         ytTEh = 0.5*bh
 
 
-        if (pari[iifclose] == 0)
+        if (fuselage.layout.taper_fuse == 0)
             xcLEh = xoLEh
             xcTEh = xoTEh
             ycLEh = yoLEh
@@ -382,7 +385,7 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
         yh[ 6] = ycTEh
 
         #Initialize seat start x-position
-        xseats0 = parg[igxshell1 ]
+        xseats0 = fuselage.layout.x_pressure_shell_fwd
         # Fuel tank
         ntank = 8
         Rtank = Rfuse - 0.1 # Account for clearance_fuse
@@ -438,7 +441,7 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
         xshell = zeros(ntank)
         yshell = zeros(ntank)
         AR = 3.0
-        xshellcenter = parg[igxshell2] - Rfuse/AR
+        xshellcenter = fuselage.layout.x_pressure_shell_aft - Rfuse/AR
         for i = 1: ntank
             fraci = float(i-1)/float(ntank-1)
             fracx = sin(0.5*pi*fraci)
@@ -450,7 +453,7 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
 
     pax = parg[igWpay]/parm[imWperpax]
 
-    wcabin = find_cabin_width(parg[igRfuse], parg[igdRfuse], parg[igwfb], parg[ignfweb], parg[igfloordist]) #Find cabin width
+    wcabin = find_cabin_width(fuselage.layout.radius, fuselage.layout.bubble_lower_downward_shift, fuselage.layout.bubble_center_y_offset, fuselage.layout.n_webs, parg[igfloordist]) #Find cabin width
     _, xseats, seats_per_row = place_cabin_seats(pax, wcabin)
     xseats = xseats .+ xseats0
     rows = length(xseats)
@@ -569,7 +572,7 @@ function stickfig(ac::aircraft; ax = nothing, label_fs = 16)
 
     # 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]),
+     parm[imPFEI], para[iaMach, ipcruise1],parg[igWMTO]/9.81/1000, parg[igb], parg[igco], parg[igsweep], fuselage.layout.radius, para[iaCL, ipcruise1]/para[iaCD, ipcruise1]),
      fontsize = label_fs, ha="left", va="top")
 
     yloc = -20
@@ -627,6 +630,7 @@ function plot_details(ac::aircraft; ax = nothing)
 
     pari = ac.pari
     parg = ac.parg
+    fuselage = ac.fuselage
     @views pare = ac.pare[:,:,1]
     @views para = ac.para[:,:,1]
     @views parm = ac.parm[:,:,1]
@@ -669,7 +673,7 @@ function plot_details(ac::aircraft; ax = nothing)
 
         # Weight build-up
         Wempty  = parg[igWMTO] - parg[igWfuel] - parg[igWpay]
-        Whpesys = parg[igWMTO] * parg[igfhpesys]
+        Whpesys = parg[igWMTO] * fuselage.HPE_sys.W
         Wlgnose = parg[igWMTO] * parg[igflgnose]
         Wlgmain = parg[igWMTO] * parg[igflgmain]
         Wtotadd = Whpesys + Wlgnose + Wlgmain
@@ -679,7 +683,7 @@ function plot_details(ac::aircraft; ax = nothing)
         WMTO  = parg[igWMTO]
 
         Wwing  = parg[igWwing]
-        Wfuse  = parg[igWfuse]
+        Wfuse  = fuselage.weight
         Wvtail = parg[igWvtail]
         Whtail = parg[igWhtail]
         Weng = parg[igWeng]
@@ -1087,6 +1091,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
 
     pari = ac.pari
     parg = ac.parg
+    fuselage = ac.fuselage
     @views pare = ac.pare[:,:,1]
     @views para = ac.para[:,:,1]
     @views parm = ac.parm[:,:,1]
@@ -1135,16 +1140,17 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
         yw[5] = bs/2.0
         yw[6] = bo/2.0
     # Fuse
-        Rfuse = parg[igRfuse]
-        wfb   = parg[igwfb]
+        fuselage = ac.fuselage
+        Rfuse = fuselage.layout.radius
+        wfb   = fuselage.layout.bubble_center_y_offset
 
-        anose    = parg[iganose]
-        btail    = parg[igbtail]
+        anose    = fuselage.layout.nose_radius
+        btail    = fuselage.layout.tail_radius
 
-        xnose    = parg[igxnose   ]
-        xend     = parg[igxend    ]
-        xblend1  = parg[igxblend1 ]
-        xblend2  = parg[igxblend2 ]
+        xnose    = fuselage.layout.x_nose
+        xend     = fuselage.layout.x_end
+        xblend1  = fuselage.layout.x_start_cylinder
+        xblend2  = fuselage.layout.x_end_cylinder
         xhtail   = parg[igxhtail  ]
         xvtail   = parg[igxvtail  ]
         xwing    = parg[igxwing   ]
@@ -1164,7 +1170,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
         xf = zeros(nnose + ntail + 1)
         yf = zeros(nnose + ntail + 1)
 
-        if pari[iifclose] == 0
+        if fuselage.layout.taper_fuse == 0
             dytail = -hwidth 
         else
             dytail = -0.2*hwidth
@@ -1224,7 +1230,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
         ytTEh = 0.5*bh
 
 
-        if (pari[iifclose] == 0)
+        if (fuselage.layout.taper_fuse == 0)
             xcLEh = xoLEh
             xcTEh = xoTEh
             ycLEh = yoLEh
@@ -1331,7 +1337,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
     yv[ 6] = ycTEv
 
     #Initialize seat start x-position
-    xseats0 = parg[igxshell1 ]
+    xseats0 = fuselage.layout.x_pressure_shell_fwd
     # Fuel tank
     ntank = 8
     Rtank = Rfuse - 0.1 # Account for clearance_fuse
@@ -1346,7 +1352,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
             xseats0 = xtanks[1] + l/2 + 1.0 * ft_to_m #move seats backwards
         elseif tank_placement == "rear"
             xtanks = [parg[igxftankaft]]
-            xseats0 = parg[igxshell1 ]
+            xseats0 = fuselage.layout.x_pressure_shell_fwd
         elseif tank_placement == "both"
             xtanks = [parg[igxftank], parg[igxftankaft]]
             xseats0 = xtanks[1] + l/2 + 1.0 * ft_to_m #move seats backwards
@@ -1384,7 +1390,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
     xshell = zeros(ntank)
     yshell = zeros(ntank)
     AR = 3.0
-    xshellcenter = parg[igxshell2] - Rfuse/AR
+    xshellcenter = fuselage.layout.x_pressure_shell_aft - Rfuse/AR
     for i = 1: ntank
         fraci = float(i-1)/float(ntank-1)
         fracx = sin(0.5*pi*fraci)
@@ -1396,7 +1402,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
 
     #Seats
     pax = parg[igWpay]/parm[imWperpax]
-    wcabin = find_cabin_width(parg[igRfuse], parg[igdRfuse], parg[igwfb], parg[ignfweb], parg[igfloordist]) #Find cabin width
+    wcabin = find_cabin_width(fuselage.layout.radius, fuselage.layout.bubble_lower_downward_shift, fuselage.layout.bubble_center_y_offset, fuselage.layout.n_webs, parg[igfloordist]) #Find cabin width
     _, xseats, seats_per_row = place_cabin_seats(pax, wcabin)
     xseats = xseats .+ xseats0
     rows = length(xseats)
@@ -1524,7 +1530,7 @@ function high_res_airplane_plot(ac; ax = nothing, label_fs = 16, save_name = not
 
     # 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]),
+     parm[imPFEI], para[iaMach, ipcruise1],parg[igWMTO]/9.81/1000, parg[igb], parg[igco], parg[igsweep], fuselage.layout.radius, para[iaCL, ipcruise1]/para[iaCD, ipcruise1]),
      fontsize = label_fs, ha="left", va="top")
 
     yloc = -20