Doodles with numbers - Brainstorming 'Nano Cub' details

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Floydr92

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No licensing required in the UK.

I believe the vehicle is subject to approval by the government or a proxy.

I answered my question about the maximum lift coefficient. In order to meet the 20 knot stall speed at 365 pounds gross weight (70 kg + my clothed weight) the lift coefficient required is 5 for the geometry in the sketch.

Please show us your source.

Calculated CL 2.9 for a gross weight of 374lbs. Off to work so I'll answer better later
 

Floydr92

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Don't forget to add the download on the tailplane to the lift required. I've never seen a wing CL of 5!
Neither have I, I think aeroER is getting his numbers mixed up a little. 2.9 is the number I'm working with. CFD predicts a little higher but I'm not confident in that result.
 

Bille Floyd

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This is my Atos , (being test-flown by a friend) ; flapped, with
spoilers, 40' span @ 34kg.

Cut the span down to 30' , and keep the flaps, with struts ; I believe
this type of wing structure , (Is) the way to go. You end up
with a Carbon D-tube , with folding carbon ribs, and a 3.2oz
Dacron sail. I can put it together in :20-min ; or it does have
an aluminum box with removable pins in it's center, to leave
the basic wing structure intact but fold-able.

I really Really Like your idea ; I see taking one of
my rigid wing Extacy's and building this as a part-103
ultralight , for American use !

Bille
 

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Bille Floyd

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And on your fuselage :
Save a Bunch of weight , and complexity, by going
with a simpler design ; like the Goat .

Bille
 

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AeroER

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Neither have I, I think aeroER is getting his numbers mixed up a little. 2.9 is the number I'm working with. CFD predicts a little higher but I'm not confident in that result.

I made a dumb error converting knots. That results in 2.8 maximum lift coefficient required in the first cut without including the balancing tail load.

2.8 or 2.9 is optimistic, too, maybe 14% high (without rooting around for a better number).
 

Floydr92

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I made a dumb error converting knots. That results in 2.8 maximum lift coefficient required in the first cut without including the balancing tail load.

2.8 or 2.9 is optimistic, too, maybe 14% high (without rooting around for a better number).
We need a little optimism with this design! 🤣
 

Tiger Tim

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It’s not really where I’d start, construction-wise, but your Nano Cub is otherwise very similar in concept to the Featherweight Champ that’s been buzzing around in my head for a few years now. I’ll be watching this thread with interest.
 

Floydr92

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Messages
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Location
Scotland
And on your fuselage :
Save a Bunch of weight , and complexity, by going
with a simpler design ; like the Goat .

Bille

Do you have any more pictures or details of your wing structure? I'm leaning towards fabric covered carbon framed wing. Maybe not with hinged ribs though.

Robert
 
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