Any thoughts pro vs con? My metal guru wants me to use 2024 but some other gents tell me I should be using 6061 for corrosion resistance.
TIA
TIA
Actually 2024-T3 is X2 stronger than 6061-T4. Common temper for 6061 is T4 or T6Any thoughts pro vs con? My metal guru wants me to use 2024 but some other gents tell me I should be using 6061 for corrosion resistance.
TIA
Steve, welcome to VAF.
Lots of members are building non Vans aircraft, myself included.
When you get that SeaRey, try on an RV for size------you might like it.
If I recall, 6061-T4 / T6 would be too brittle to bend vs 2024-T3. The bend at the bottom adds rigidity to the panel.
Even with holes in it, it is part of the structure and will pick up loads. Take the panel out and push on the sides of the fuselage where the panel was you took out. The fuselage will flex more than when it was in. The instrument panel ties to the side of fuselage longerons which provides laterally stability. When longerons are in compression they need things to keep them from buckling or crippling... With the panel (which has an angle at the bottom and is stiff) the fuselage will have more stiffness overall. Is it critical? Not really, but without doing analysis you don?t know what it contributes.Rarely if ever is the instrument panel relied on as a load bearing piece, because you punch so many holes in it - its just an item to mount things in.
Even with holes in it, it is part of the structure and will pick up loads. Take the panel out and push on the sides of the fuselage where the panel was you took out. The fuselage will flex more than when it was in. The instrument panel ties to the side of fuselage longerons which provides laterally stability. When longerons are in compression they need things to keep them from buckling or crippling... With the panel (which has an angle at the bottom and is stiff) the fuselage will have more stiffness overall. Is it critical? Not really, but without doing analysis you don?t know what it contributes.