Try it again?

this one is a 76 sq. ft wing which is not the exact right wing
for this plane, but the worksheet was already done-so...what.

No idea how the columns will hold up on the net, but .....
it's worth a try...

The spar caps are 1-1/5" X 1/8" 6061 with 1-1/2" x 1/8"
6061 straps layered to the indicated (interpreted) thickness.

Bruce bolted his spar, which produced a very straight spar
assembly.

Hammering big rivets into small structures will invariably
induce some distortion.

We are doing is a beam spar rather than a proper box, so the
sheer web dimension should be doubled.

And?
No promise that any of this is close to correct...

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X-Wing SPAR Build .58 R.Lamb 2001
Project Name L-One V
Run time: 01-10-2006 at 10:43:10

Wing Span [ft] 17.00 Root Chord [ft]
5.00
Wing Area [sqft] 76.50 Tip Chord [ft]
4.00
Chord thickness [%] 12.00 Mean Chord [ft]
4.50
Gross Wgt [lb] 888.00 Aspect Ratio [#]
3.78
Lift (Vs) [lb] 888.00 Wing Loading [lb/sqft]
11.61
V(min) [mph] 59.04 Max CL [#]
1.30
Load Factor [G's] 4.00 Spar Width [inches]
1.50
Cap Compression [psi] 66,000 Shear Web [psi]
10,000
Thickness [% of Chord] 12


Sta W.STA. AIR LOAD SHEAR MOM FTLB
num FT PPF LB FT.LB
1 0.000 232.000 1776.000 7268.000
2 0.850 236.000 1580.000 5842.000
3 1.700 241.000 1389.000 4580.000
4 2.550 246.000 1201.000 3479.000
5 3.400 250.000 1018.000 2536.000
6 4.250 255.000 838.000 1747.000
7 5.100 260.000 663.000 1109.000
8 5.950 264.000 491.000 618.000
9 6.800 269.000 323.000 272.000
10 7.650 273.000 159.000 67.000
11 8.500 278.000 0.000 -1.000

Spar weight parameters:

Sta W.Sta. SPAR HGT CAP THK WEB THK
num FT IN IN IN
1 0.000 5.760 0.306 0.031
2 0.850 5.645 0.251 0.028
3 1.700 5.530 0.201 0.025
4 2.550 5.414 0.156 0.022
5 3.400 5.299 0.116 0.019
6 4.250 5.184 0.082 0.016
7 5.100 5.069 0.053 0.013
8 5.950 4.954 0.030 0.010
9 6.800 4.838 0.014 0.007
10 7.650 4.723 0.003 0.003
11 8.500 4.608 -0.000 0.000

Shear web thickness is for a box type spar. For single web, double
it.

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