A number of classic and homebuilt fabric-covered designs, including the Volksplanes, use an aluminum leading edge to bridge the gaps between the wing ribs and help the fabric hold the airfoil shape a little better. In some cases, plywood is specified as an alterative and some have even used fiberglass, Kevlar and carbon fiber. Note that I am not talking about D-cell spars or stress-skin construction, just aerodynamic leading edge sheeting.
This clip and site demonstrate some informal testing of the impact resistance of each type, though I do find it odd that they don't compare coverings of the same weight.
Source: http://www.davisaeroparts.com/research-and-development.html
In the case of the VP-2, the plans specify 24ST .020 aluminum (equivalent to 2024T3 as far as I can tell) but also suggest 1/16" plywood as an alternative. I terms of weight, the aluminum weighs 0.288 lb/sq ft and 1/16" mahogany aircraft plywood about 0.1875 lb/sq ft.
If those numbers are right, then that certainly seems to argue in favor of the plywood. Is there anything I am missing? Anyone every messed around with composite leading edges in this type of application?
Cheers,
Matthew
This clip and site demonstrate some informal testing of the impact resistance of each type, though I do find it odd that they don't compare coverings of the same weight.
Source: http://www.davisaeroparts.com/research-and-development.html
In the case of the VP-2, the plans specify 24ST .020 aluminum (equivalent to 2024T3 as far as I can tell) but also suggest 1/16" plywood as an alternative. I terms of weight, the aluminum weighs 0.288 lb/sq ft and 1/16" mahogany aircraft plywood about 0.1875 lb/sq ft.
If those numbers are right, then that certainly seems to argue in favor of the plywood. Is there anything I am missing? Anyone every messed around with composite leading edges in this type of application?
Cheers,
Matthew
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