I am looking for a diagram that shows the different diameters of various nozzle openings, including Rocketdyne's F1 (150 inches) SpaceX's Merlin (66 inches), the Air Force's Delta IV Heavy, and NPO Energomash's Proton-M (59 inches). Those ones are rather popular and easier to find, but I am wondering if anyone has a list of different engines and their different characteristics.
My theory is that engine size compared to launch vehicle weight is going to decrease over time, especially as efficiency rises. If I had some more data I might be able to show this to be true. Thanks for any help.
Let me clarify a little bit. I want to see if, for a given launch vehicle weight, the diameter of the engine nozzle has decreased slowly over time, as engines become more efficient and use lighter materials. As such, if I have different nozzle diameters at different time periods of high engine usage, there may be a trend through time. Plus, it would just be cool to see this information, and see how different engine characteristics have changed through time. I want to see what sort of trends like this exist among other engine characteristics, to see how the technology evolves. I would also make this comparison against thrust.
Lastly, I am really interested in engine design, and understanding how technological advancements change the dimensions and components will help a lot.