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  1. D

    Schrenk's method part deux

    Hey, I have got some explanation of schrenk's method in the following link. http://www.uotiq.org/dep-MechanicsandEquipment/lecture/Aircraft%20Engineering/fourth_class/Aircraft%20Structure%20and%20Design3.pdf Have a look please. . There are two things that I did not understand in it. 1. When...
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    Help? Home wing load testing

    Yes, you are right autoreply!! And now i m thinking that i ve asked the dumbest questions ov all.:P Because as I was thinking, force distribution along the span will be linear, it will not be elliptic in any way or near it.
  3. D

    Schrenk's method part deux

    I m still exploring threads
  4. D

    Help? Home wing load testing

    I m gona ask a stupid question. . So be patient!! What if, we do not use sand bags or whiffler tree (beams) and instead use an airbag filled with a pressurized air. I mean its just an idea that is popping up in my mind that calculate the pressure from your loading and then attach a bag shaped...
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    Schrenk's method part deux

    Well but why to wait me for a picture, with some dimensions altered it is more or less Rutan's Long Ez. Its outer wing is to be tested. I hope you have a clear idea know. :)
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    Schrenk's method part deux

    Ultimate load is 2.33g and applying SF ov 1.5, its 3.5gs. And yes wing has been built and I ve to figure out, how it is going to be tested for the loading that I described in the above post. And unfortunately, I dun ve any pic yet. . :(.
  7. D

    Schrenk's method part deux

    C-root = 1058mm C-tip =508mm b/2 =2580 mm Mass of the bird is 630Kg, using L=W and since normal load is 3.5gs, So L=630*10*3.5= 22050 N and for Half wing it would be half and therfore L/2= 11025N. I didn't use any Cl or angle of attack. Actually we need to do the structural testing of the wing...
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    Schrenk's method part deux

    Can't see an upload tab. . How to upload a pic :s
  9. D

    Schrenk's method part deux

    Amen. Thank you So much Brother for your supporting words. Okay, if I am okay till now then let's say I have 7000N lift (Predicted by L=Wt of whole aircraft) on a wing with no twist. By looking at the both equations, it seems that at root, magnitude of the lift force will be equal to the value...
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    Schrenk's method part deux

    Thank you so much Autodidact, your explanation of this technical memorandum is very helpful, as I am a new into this field. I want to ask a question here, that if Wings don't have twist then what I could figure out is that as shown in figure 1 of your post, only elliptical function...
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