I appreciate the response; thanks. Just as more of an FYI this is what I've been using so far:
http://www.braeunig.us/space/sup1.htm
https://www.risacher.org/rocket/eqns.html
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...