Rocket Design Resources

This site is hosted by NASA Glenn Research Center and has the isentropic equations that are used to find the mass flow rate, exit mach number, exit temperature, exit pressure, exit velocity, and thrust of a rocket engine.

This site is similar to the NASA Glenn page but it goes more indepth on a few things and has some extra equations to find the area of the throat and exit as well as a method for chamber sizing and calculating hoop stress for the chamber.

Robert Watzlavich has one of the most complete project blogs I've ever seen. He has massive lists of suppliers, most if not all of his design iterations, videos and pictures of testing and hardware, as well as many design resources. He is a very skilled engineer and his site has been used as a resource by everyone I've talked to that does amatuer liquid rocketry.

NASA CEA is an online tool that can be used to find combustion parameters inside of rocket engines using any propellants. This tool is very useful when designing a rocket engine and is entirely free to use.

This is a python module that interfaces with NASA CEA and is very useful when trying to integrate NASA CEA results into design and analysis tools coded with python. It can be a hassle to get working due to the C++ and FORTRAN compilers that must be installed in parallel, but I think it's usefulness outweighs the time and frustration that are required to get the integration working.