Based on a section modulus of 18.5 in3 and yield strength of spruce at 5000
Psi, the center spar should yield at 92500 lb in. bending moment. I don't
know how that translates to wing load.

On Feb 22, 2015 4:58 PM, <PPaulVsk at aol.com> wrote:
>
> Just an idea. We have a gathering coming up in September.  I would
imagine there is a set of fwd spars lying around gathering dust somewhere.
If we can get them to McMinnville with some sandbags and do our on test. I
would be willing to pitch in to help defray the cost.
>
> I might be able to talk to Eric at Wicks to donate some of there
scrap spruce if someone would like to build a AS5048 Spar. We would just
need a center and one outboard spar.
>
> Paul Visk
> Belleville Il.
> 618-406-4705
>
> In a message dated 2/22/2015 10:23:07 A.M. Central Standard Time,
krnet at list.krnet.org writes:
>>
>> On Sun, Feb 22, 2015 at 1:29 AM, Flesner via KRnet <krnet at list.krnet.org>
wrote:
>> >
>> >>
>> >> The Spreadsheet says we should be using aluminum spars to make more
>> >> than 2G load factors.
>> >
>> > ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++
>> >
>> > It's been a long held belief that the WAF's were the weak point in the
KR
>> > spars.  I've had the opportunity to inspect 3 crashed KR's,
unfortunately
>>
>> both front and rear spars together can easily take 3.8G at 1200 lbs
>> mtow. but thats a rough calculation. i'm actually overestimating the
>> stresses because tapered wings have more or less 10% lower bending
>> moments than rectangular wings overall. I was assuming a rectangular
>> wing.
>>
>> a more accurate computation will require more accurate load
>> distributions with flap and aileron deflections considered. only
>> shrenk's approximation and similar procedures can do that.
>>
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