Doodles with numbers - Brainstorming 'Nano Cub' details

[Floydr92]

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

 

[raytol]

Don't forget to add the download on the tailplane to the lift required. I've never seen a wing CL of 5!

 

[Floydr92]

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]

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

 

[Bille Floyd]

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

Bille

 

[AeroER]

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]

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]

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]

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

 

[Tiger Tim]

Do you have any more pictures or details of your wing structure?

On the Goat? Plans are available free online for it and some similar gliders and powered ULs by Mike Sandlin.

Goat Page

m-sandlin.info