Profiling of Supersonic Rocket Engine Nozzles Subject to Compliance with Real Combustion Product Properties Using the Grid-Characteristic Method

Differential equations for calculating laminar flows of combustion products in supersonic nozzles are proposed. Solutions to the equations for calculating laminar flows in supersonic nozzles are found in the form of characteristic equations and compatibility equations. An algorithm for solving the problem of profiling supersonic nozzles subject to compliance with the real properties of combustion products using the grid-characteristic method is developed.