Does your direct experience support that industrially manufactured 1/2-inch thick Nomex honeycomb sandwich panel could be up to this project?
If you had to press me, I'd say no. It looks like the material has only a single layer of fiberglass and from what I have seen simulating laminates that won't be sufficient for fins of the span you are trying to achieve. You likely need a couple layers of medium weave carbon fiber applied at 45 degree angle, or potentially better three layers of unidirectional fiber applied a 0, 45 and 90. But, in the end the three sentences above are "crap" as they are stabs in the dark not knowing all your parameters as will be the comments of most others, as pointed out earlier. Why? Because, few, if any, have built a rocket of the size you are considering matched with the fin material you have in mind. Closest match for me is
a rocket I'm working on now that uses 1/4"
ACP Composites Nomex honeycomb-carbon fiber; but the rocket is only 6" diameter and the fin profile is considerably different. But a 1/4" fin is likely not appropriate for a rocket of the size you are considering.
For a 11.5" V2 I am also in the process of building, I will be using two 1/4" lite ply panels with cut outs to provide a frame which will have 1/4" styrofoam inserted; these panels will then be sandwiched with one layer of carbon fiber in the middle and two layers on the outside of each giving me a finished thickness of ~0.575. I have not completed simulation of that stackup and the rocket flight profiles, but I believe I will be in the ballpark. But again, I will verify this for my rocket, its dimensions and profiles only. The application of the same stackup on a different rocket and its specific flight profile will be completely different.
I have AeroFinSim. Problem is that only accepts trapezoidal fin shapes. So I can't exactly simulate my fin.
Yes, but your fins are not too far off from a trapezoid, just make sure your span is close, shape is approximate and the overall area is represented.
But I did make an approximation to my design and materials. AeroFinSim's flutter velocity is below RockSim's maximum velocity prediction.
Well if that is the case, then you should be worried and take the simulation one step deeper. There was a recent experience of a large rocket where, from all appearances, the preflight homework was not done. Anyone that is considering launching a rocket of any significant size owes it to the rocket community to do the preflight homework to assure stability and structural integrity of their design/build (but that is just my opinion).
I also agree that skins play an important and complex role in ultimate panel properties. But please consider that, as a fin bends and twists, the shear properties of the core come to dominate "stiffness." A fin that's not stiff has lower natural frequencies that may become excited at lower velocities. That is why I've focused, perhaps fecklessly, on shear modulus.
From what I have seen in my simulations flutter is most impacted by fin thickness, then fin shape, then skin material characteristics then the impact from other things (adhesive, fillet shape, core material) fall off considerably. I am not an expert in this area, but for a limited view you can take a look of an
excerpt from my L3 documentation that provides a commentary on the flutter analysis I did for that design.