Liquid Rocket engine design is quite complicated and idealised and assumed theories rarely get sufficient validation. In an effort to verify/validate newer/untested fuels to be used in engine designs, can one adapt data of present engines from similar fuels? If so, what are the parameters most likely to be affected and which are the parameters insensitive to the fuel being burnt(if any)? I see that the engine cycle is quite important, but to compare the performance of cryogenic methane for example in comparison to existing engines (gas generator, closed expander, staged combustion atleast)
TL:DR I'm looking for a sensitivity analysis for rocket engines for various design parameters across different fuels.
P.S. Has anyone used Rocket Propulsion Analysis (RPA) for such an analysis? How accurate is it?