So I'm not very experienced in terms of aerospace design (at all), but I've been looking for a formula to help me estimate nozzle thickness given temperature at the throat, exhaust area, and choice of nozzle material (which I still have yet to decide) etc.. I have found the general guideline that the nozzle thickness is roughly the same as the thrust chamber thickness, but I'm looking for something a bit more specific; this is in case for say my choice of nozzle material differed from that of the thrust chamber et al.. I'm really approaching this from more of a theoretical point of view and so am light on the details. Anyway I was wondering if anyone knew of a formula or could point me in the right direction. Thanks.
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