in Australia.'
Subject: Re: [Aus-soaring] B787
Except that was a 777 in the movie I think.
The failure occurred at around 2.66% greater than what the designed it
to fail at. (The structure needs to be tested to not fail at 150% of
design limit load (this point is called ultimate load))
I am told
: [EMAIL PROTECTED]
[mailto:[EMAIL PROTECTED] On Behalf Of Tom
Sent: Thursday, 28 June 2007 7:03 PM
To: Discussion of issues relating to Soaring in Australia.
Subject: Re: [Aus-soaring] B787
The fact that it said 1995 at the bottom is a clue :-)
- Original Message -
From: Dave [EMAIL PROTECTED
Dave wrote:
**maybe it could be
bend far enough for the wingtips to touch above the fuselage—
I guess that's one way to minimize tip vortices.
- mark
I tried an internal modem,[EMAIL PROTECTED]
in Australia.
Subject: Re: [Aus-soaring] B787
Dave wrote:
**maybe it could be
bend far enough for the wingtips to touch above the fuselage-
I guess that's one way to minimize tip vortices.
- mark
I tried an internal
to Soaring in Australia.
Subject: Re: [Aus-soaring] B787
Dave wrote:
**maybe it could be
bend far enough for the wingtips to touch above the fuselage-
I guess that's one way to minimize tip vortices.
- mark
I tried an internal
.'
Subject: Re: [Aus-soaring] B787
They did break it see:
http://www.youtube.com/watch?v=6Uo0C01Fwb8
What a noise!!
Failed at 154% max load!
Dave
-Original Message-
From: [EMAIL PROTECTED]
[mailto:[EMAIL PROTECTED] On Behalf Of Mark
Newton
Sent: Wednesday, 27 June 2007 3:36 PM
.'
Subject: Re: [Aus-soaring] B787
Except that was a 777 in the movie I think.
The failure occurred at around 2.66% greater than what the designed it
to fail at. (The structure needs to be tested to not fail at 150% of
design limit load (this point is called ultimate load))
I am told that at Boeing
Hi all,
So this is where all the carbon fibre is going!
http://blog.wired.com/wiredscience/2007/06/the-new-boeing-.html
Quote
Boeing has completed static testing of a three-quarter wingbox, but
engineers are still considering whether to limit testing of the full wing to
a 150% load limit held
