Ron B.
F4Fguy
Bill:
If you mean two plys of 1/32" laid one over the other,one layer of 1/16" will be just as strong.If you mean cross ply,then you're right.My last Macchi fuse was 39"lg x 9"dp x5"wd.It consisted of two plys of 1/32 6# laid 30deg.to each other and weighed 6oz.with the bulkheads(3plys crossed 1/32" ~4"apart)there was no other internal structure from the wing leading edge back.
On the other hand This was a royal pain to do!It was also structural overkill in most areas.Since then my airplanes have been done with molded 1/20" sheets formed on a blue foam mold and assembled in a jig,laminated in high stress areas to two or even three layers.This gives the best use of material on a strength to weight basis.As an example,the WildcatIIwas three ply to the wing H.P.,two on the sides only to just behind the flap,onelayer from there to the stab,and two under the stab platform.With one wing supported at the fuse side,you could hold the plane level by the stab with no percievable twist.
While on the subject,I've done some primitive testing on various layups(enough to convince myself)with unsurprising results.Carbon,glass,silkspan,etc.reinforcements are dependent on the ahesive,that is,their tensile strength and effectiveness goes up as the adhesive strength(dope<urethane<polyester<epoxy).Stiffness goes up with distance from the neutral axis,as well as with adhesive.None of the materials were effective as a center ply in stiffness.That is to say two plys glued together had the same deflection as the ones with carbon veil etc.in the center.Two plys sans carbon etc.showed some improvement over one ply of the same thickness,probably because grains are always slightly crossed even when samples are from the same sheet.
Putting the veil on both surfaces of the outside is very much a different story.Here deflection was very low for the same load and in proportion to the material and the adhesive.Unfortunately weight also goes up unless adhesive is rigidly controlled.The only effective way I've found is bagging with a peel ply and an absorbent breather ply(not really very user friendly).
Veil on one surface fell,as expected,somewhere in between,with a heavy bias to the bare two ply with the same adhesive.Obviously load direction made a big difference here,carbon/epoxy was almost non-effective on the side opposite the load(this would be the inside of a fuse).
All of the above is relative only to local loads.In a fuselage structure placement of the veil is relatively unimportant as the skins are stressed as part of the section modulus of the whole fuselage.This is one good argument for FAT airplanes.
In sum,I'd say that,as presently used by most,veil is good to stop skin deflections such as"skeletoning"but,it doesn't do much in terms of overall strength.Even then I believe molded balsa compound curves are more effective.
If you eliminate the balsa altogether........that's another story for another time,but it can be interesting.