Improvements to RBCC engine performance analysis model

Improvements to former RBCC engine performance analysis model was investigated. Thermodynamics calculation model for primary rocket was established by adopting the Minimum Gibbs Energy method for primary rocket chamber, and the frozen flow assumption for nozzle flow. Thermodynamics calculation was carried out for primary rocket which uses the propellant of H₂O₂(L)/JP-10(L). Comparison was made with the results obtained from those published softwares, such as CHEMKIN and CEA, and the validation of improvements verificated. Performance analysis model for aftbody was established by using CFD code to solve the 2-D Euler equations. An automatic calculation strategy for aftbody performance analysis was designed on the basis of the programming interface of CFD code and PYTHON script language, automating the geometry modeling, mesh generation, boundary condition definition, CFD solver configuration, CFD equations solving and performance parameters calculation for aftbody.