Doodles...

Richard,
What software did you use to design the aircraft? The aircraft looks pretty damn good.
Jim Williams






UOTE=Richard Lamb]Well, since you asked...

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...

================================================== ======================

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.

================================================== ======================[/quote]

Richard,
What software did you use to design the aircraft? The aircraft looks pretty damn good.
Jim Williams






UOTE=Richard Lamb]Well, since you asked...

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...

================================================== ======================

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.

================================================== ======================[/quote][/quote]

Jim Williams wrote:
Richard,
What software did you use to design the aircraft? The aircraft
looks pretty damn good.
Jim Williams


Mr. Williams is obviously a man of good taste and culture.
Probably an Ace pilot and a handsome devil too...
Thanks, Jim.


CAD:
The drawings are done with Design CAD 2000. My choice.
I started with the DOS version of DC - golly - 25 or 30
years ago, now. That's a really nice package too. IMHO,
way better than Autocad V10, (which I also bought way back
when?).
Both put lines on paper, but so does a pencil.
Drawing a smooth spline, on the other hand...

There was a real cool release of this program a while back
under the name ModelCAD. It was optimized to design model
airplanes(!). Tapered wing rib patterns et al.
I haven't played with it, but I'd love to if anybody out
there has a copy.

I don't think it matters much what CAD package you pick,
drawing in 3D is a little higher hurtle to get a leg over.

Or maybe it's just a question of what you learn first?
I know kids who can do beautiful 3D, but can't project
a 3 view on paper. Dunno...


Animations:
The animations are made from CAD screen shots.
(rec.aviation.homebuilt - NOT - Industrial Light and Magic)

Draw, render, save pic,
move parts, render, save pic,
repeat until done,
or until you goof,
or just can't stand it any more.

The DC programing language is BASIC-like (rather than
Autocad's Lisp interpreter?). I haven't tried to write
anything to do this kind of animation, but it's certainly
possible.
For any kind of ILM style animation, I think you'd have to.

The elevator and aileron animations are only eight frames
each (IIRC?). Four for each side. They are simply
repeated in the reverse order to show the return paths.
They were stitched together with GifAnimator.
That part is pretty simple, really.


Analysis: (and back on topic?)

The stress calculations are provided by a custom program
(originally published in Sport Aviation a LONG time ago).

I got it working (I think), and added a menu system to
allow easy editing of wing parameters, weights, G limit,
material strength, spar width, etc.
Plug in your numbers and it grinds out the details.

One of the things it creates is a spar size table that
_is alleged_ to be minimum material dimensions to carry
the given load.

But like Stealth, I wonder if it can be trusted!

And, like Stealth, I'd like to have it evaluated by
someone who knows what they are doing before diving off
the deep end.

So...

I thought of one point that might could be calibrated -
Vans RV-9.

IIRC, RV-9 spar caps are milled from a single bar of aluminum
and stepped thicker at the root. We also know how thick the
spar shear webs are - from the plans.

All we'd need the spar dimensions from the plans,
and the following data:

Span [ft] [ ] Span Load [lb/ft] [calc]
Area [sqft] [ ] Area Load [lb/sqft] [calc]
Chord root [ft] [ ] RN root [mil] [calc]
Chord tip [ft] [ ] RN tip [mil] [calc]
Chord MAC [ft] [calc] RN mean [mil] [calc]
Aspect [#] [calc] Max CL [#.##] [ ]

Gross Wgt [lb] [ ] Stall Speed [mph] [calc]
Design G's [#] [ ]

Wing Thick[%chord] [ ] Spar Compr [psi] [ ]
Cap Width [in] [ ] Spar Shear [psi] [ ]


Any takers?

Richard

Mr Lamb knows me very well. Your too kind, but right. Get the numbers right on the design and I'll start cuting metal .
Jim

Originally Posted by Richard Lamb

Jim Williams wrote:
Richard,
What software did you use to design the aircraft? The aircraft
looks pretty damn good.
Jim Williams


Mr. Williams is obviously a man of good taste and culture.
Probably an Ace pilot and a handsome devil too...
Thanks, Jim.


CAD:
The drawings are done with Design CAD 2000. My choice.
I started with the DOS version of DC - golly - 25 or 30
years ago, now. That's a really nice package too. IMHO,
way better than Autocad V10, (which I also bought way back
when?).
Both put lines on paper, but so does a pencil.
Drawing a smooth spline, on the other hand...

There was a real cool release of this program a while back
under the name ModelCAD. It was optimized to design model
airplanes(!). Tapered wing rib patterns et al.
I haven't played with it, but I'd love to if anybody out
there has a copy.

I don't think it matters much what CAD package you pick,
drawing in 3D is a little higher hurtle to get a leg over.

Or maybe it's just a question of what you learn first?
I know kids who can do beautiful 3D, but can't project
a 3 view on paper. Dunno...


Animations:
The animations are made from CAD screen shots.
(rec.aviation.homebuilt - NOT - Industrial Light and Magic)

Draw, render, save pic,
move parts, render, save pic,
repeat until done,
or until you goof,
or just can't stand it any more.

The DC programing language is BASIC-like (rather than
Autocad's Lisp interpreter?). I haven't tried to write
anything to do this kind of animation, but it's certainly
possible.
For any kind of ILM style animation, I think you'd have to.

The elevator and aileron animations are only eight frames
each (IIRC?). Four for each side. They are simply
repeated in the reverse order to show the return paths.
They were stitched together with GifAnimator.
That part is pretty simple, really.


Analysis: (and back on topic?)

The stress calculations are provided by a custom program
(originally published in Sport Aviation a LONG time ago).

I got it working (I think), and added a menu system to
allow easy editing of wing parameters, weights, G limit,
material strength, spar width, etc.
Plug in your numbers and it grinds out the details.

One of the things it creates is a spar size table that
_is alleged_ to be minimum material dimensions to carry
the given load.

But like Stealth, I wonder if it can be trusted!

And, like Stealth, I'd like to have it evaluated by
someone who knows what they are doing before diving off
the deep end.

So...

I thought of one point that might could be calibrated -
Vans RV-9.

IIRC, RV-9 spar caps are milled from a single bar of aluminum
and stepped thicker at the root. We also know how thick the
spar shear webs are - from the plans.

All we'd need the spar dimensions from the plans,
and the following data:

Span [ft] [ ] Span Load [lb/ft] [calc]
Area [sqft] [ ] Area Load [lb/sqft] [calc]
Chord root [ft] [ ] RN root [mil] [calc]
Chord tip [ft] [ ] RN tip [mil] [calc]
Chord MAC [ft] [calc] RN mean [mil] [calc]
Aspect [#] [calc] Max CL [#.##] [ ]

Gross Wgt [lb] [ ] Stall Speed [mph] [calc]
Design G's [#] [ ]

Wing Thick[%chord] [ ] Spar Compr [psi] [ ]
Cap Width [in] [ ] Spar Shear [psi] [ ]


Any takers?

Richard

Filled in WingSpan and GrossWeight from Vans web site.
IIRC, Van uses a 23012 airfoil?
If so, the 12% stays, and I'd guess CLmax of about 1.3.

Wing Chord?
Spar cap materials?



Span [ft] [ 28] Span Load [lb/ft] [calc]
Area [sqft] [ -- ] Area Load [lb/sqft] [calc]
Chord root [ft] [ ? ] RN root [mil] [calc]
Chord tip [ft] [ ? ] RN tip [mil] [calc]
Chord MAC [ft] [calc] RN mean [mil] [calc]
Aspect [#] [calc] Max CL [#.##] [ ?.??]

Gross Wgt [lb] [1600] Stall Speed [mph] [calc]
Design G's [#] [ ? ]

Wing Thick[%chord] [12%?] Spar Compr [psi] [ ?? ]
Cap Width [in] [ ? ] Spar Shear [psi] [ ?? ]


Any takers?

Richard

"Richard Lamb" wrote in message
. net...

Filled in WingSpan and GrossWeight from Vans web site.
IIRC, Van uses a 23012 airfoil?

Richard............

I think Van uses a 23013. The Emeraude uses a 23012. That way I can go
"Neener, neener" at my buddy's RV-4 (as he goes screaming past me).

Rich S.

Rich S. wrote:
"Richard Lamb" wrote in message
. net...

Filled in WingSpan and GrossWeight from Vans web site.
IIRC, Van uses a 23012 airfoil?


Richard............

I think Van uses a 23013. The Emeraude uses a 23012. That way I can go
"Neener, neener" at my buddy's RV-4 (as he goes screaming past me).

Rich S.


Thanks, Mr. S.


Now would somebody measure the wing chord?

Jim Williams wrote:
Richard,
What software did you use to design the aircraft? The aircraft
looks pretty damn good.
Jim Williams




I was sitting here the other night, before the phone line was
installed, taking an imaginary walk around an imaginary airport
looking at the imaginary airplanes, and I had a thought -
"I gotta get a life!"

http://home.earthlink.net/~cavelamb/!tour(1).jpg

Richard Lamb wrote:

http://home.earthlink.net/~cavelamb/tour1.jpg

unix hates me...

Richard Lamb wrote:

Richard Lamb wrote:

http://home.earthlink.net/~cavelamb/tour1.jpg

unix hates me...
My unix (linux) had no problem. Nice Drawing when so you start building? ;-)
John