I'll remember this for the next go! Fuselage rear / vertical tail moulds.Try a chlorinated polyolefin adhesion promoter.
Aluminium would be better because it doesn't conform to any little imperfections so well, but by the same token getting it right into the tight curve at the nose is a problem. Of course the nose is going to be smothered in micro and sanded anyway but lets not let that sort of logic derail my cunning plan! A serious issue with aluminium is that it's actually quite hard getting a big sheet delivered without at least one ding in it.Actually, if you use .016" aluminum instead of plastic, it will be stronger, hold the airfoil better, and probably cheaper.
Sportplane builder bought and should arrive next week - thank you for the recommendation.So IMHO start with the EAA Bingelis books immediately, and then research and seek out any other books available on light aircraft design.
Question again: the top skin is a lot more curved than the bottom skin and trying to whet out the carbon while stuck to the top of a bit of PVC foam that's not 'laying down' in the mould is annoying and is likely to cause all sorts of problems. So which of these should I do, or something else?
a. heat form the PVC core to the mould shape somehow then wetlay both sides and bag.
b. outer skin, add PVC, bag then do the inner skin in a separate operation.
c. Something else.
And while looking for hardware info I came across a PDF of a Sydney Camm (designer of the Hawker Hurricane) book on aircraft construction from 1919!
I had heard of 'The Glider' but not actually got hold of a copy. Thank you for reminding me / pointing me in the right direction - I found a PDF & I'm going to see if I can add that to my Kindle for some holiday reading!Hi Foundationer,
Sir Sydney Camm a great designer.
Have you seen this book, The Glider by Stelio Frati?
I think you would find it very interesting and maybe relevant to your project. I couldn't attach it, please Google it.
That's interesting - thanks! First thing I noticed is that the 'allowed' strength he's quoted (from VLA ACJ 572(b)) for carbon appears to be 20% of the strength that's actually quoted by Marske etc. for Graphlite.Sorry to load up your kindle but this is an interesting project with lots of detail on its main spar which uses protrusions.
MITE wing design and construction.pdf