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LSA on biplane aircraft

 
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Rafael Bueno



Joined: 06 Jul 2006
Posts: 8

PostPosted: Wed Aug 02, 2006 8:34 am    Post subject: LSA on biplane aircraft Reply with quote

Does anybody know a method for biplanes spanload distribution that is accepted for LSA certification, like Schrenk method is accepted for monoplane wings?
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Rafael Bueno

www.edraaeronautica.com.br
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Rafael Bueno



Joined: 06 Jul 2006
Posts: 8

PostPosted: Thu Aug 03, 2006 12:02 pm    Post subject: Ask FAA Reply with quote

Is there a way that I can get in contact with FAA to solve the above question for me?
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Rafael Bueno

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Rafael Bueno



Joined: 06 Jul 2006
Posts: 8

PostPosted: Fri Aug 11, 2006 5:08 am    Post subject: Already done Reply with quote

I`ve already found the answer.

Thanks erveyone.

Best Regards
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Rafael Bueno

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cheapskate



Joined: 08 Jun 2006
Posts: 7
Location: Kansas

PostPosted: Sat Aug 12, 2006 11:26 am    Post subject: Reply with quote

Would you please share what you learned, some of us are pondering the same things, thanks, Cheapskate
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Rafael Bueno



Joined: 06 Jul 2006
Posts: 8

PostPosted: Wed Aug 16, 2006 5:06 am    Post subject: Reply with quote

Well, I just followed the loading method presented on AC.23-19, par. 23.301

Biplane designs. These airplanes require special aerodynamic load criteria. A previously used typical approach includes:

Developing an equivalent single wing (cellule), which aerodynamically represents the biplane wings. Civil Aeronautics Manual 04 (CAM 04), paragraph 217, provides an acceptable method unless the biplane has an unusual amount of stagger or decalage. Also, see CAM 04, Appendix III.

Defining wing and tail loads from part 23 load conditions using the equivalent single wing.

Distributing the equivalent single wing load between the upper and lower biplane wings. CAM 8, paragraph 212, provides an acceptable method for biplanes with no decalage.

Distributing the individual wing-loads spanwise using a method such as Schrenk or ANC-1. (See Figure 1.)

Instead of using CAM 8, I used the NACA TR 458 to distribute equivalent loading on both wings, because CAM 8 does not take twist in account of the effect.
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Rafael Bueno

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Rafael Bueno



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PostPosted: Wed Aug 16, 2006 5:13 am    Post subject: Sorry Reply with quote

Sorry! There is an error on my last post. I used the NACA Report because CAM 8 doesn`t take in account the effect of decalage
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