No, not like fabric, it'll be a rigid skin, so more like metal. Will need very few ribs behind the spar. While looking for something to build a FAR103 from, I found that the problem is the tradeoff between weight and abuse resistance. Strong enough for 103 flight surfaces are fragile, Hangar rash resistant surfaces get heavy, fast. Coroplast will take a heavy blow and bounce back. Fabric is the only really light way to build, but it needs lots of ribs and sags between them. i was hoping for a laminar wing, but coroplast over a carbon spar is going to be so much easier to build, it seems a good idea for an experimental first design.
I'm also a contrary sod who likes to be different. Lets face it, if I do start building a coroplast aircraft, you lot are going to be glued (NOT riveted!) to the build thread! I'm kinda busy right now and lack a workspace, but maybe next week, some of my coroplast stash and some simple moulds will find their way into the oven. Once I fix the thermostat...
From Coroplast website:
Density, g/cc ASTM-D782A-2 0.90
Notched Izod Impact (FT-lbs/in.) ASTM-D256-A @ 70 degrees F 3.0
Tensile Strength at Yield (psi units) ASTM-D638 2in/min. 4000
Elongation at yield (%) 10
Deflection Temp. degrees F 66psi 194
Water Absorption - 24 hrs, % ASTM-D570 0.02
Falling Weight Impact Strength @ -29degree F (ft.lbs.) 23
Coefficient of Linear Thermal Expansion (MM/MM/C x [10 to the -5th])
-30 degrees C to 0 degrees C 12
0 degrees C to 30 degrees C 14
30 degrees C to 60 degrees C 21
Normal temperature performance range -17 degrees F to 160 degrees F
Melting point 162 degrees C, 324 degrees F
Polypropylene wikipedia properties as first guess for E:
Modulus, GPa 1.3-1.8
I'll test for the actual modulus at some point. that'll be easier if I'm using a known brand and dimensions rather than my roadside harvest...