Mathematical modeling and experimental investigations of oxygen-methane fuel combustion at coaxial-jet supply into the combustion chamber of liquid-propellant rocket engine

The numerical results are presented for the case of coaxial-jet supply at the different ratio of mass component velocities at the combustion chamber inlet with the constant and variable relationship of oxygen-methane components. The experimental investigations of coaxial-jet mixing elements as part of the model setup chamber operating on corrosive producer gas and gaseous methane were carried out. A qualitative pattern of the $ overline {rho u} $ overline {rho u} parameter influence on the chamber economic feasibility was obtained: as $ overline {rho u} $ overline {rho u} decreases, the combustion efficiency coefficient grows.