In the present Paper, the simulation of the flow inside an experimental GOX/GCH 4 rocket
thrust chamber is undertaken. The combustor's injector consists of seven individual coaxial …

Although thermal convection is omnipresent in nature and technology and serves important
purposes in various energy transport systems, whether convection can be viewed as an …

One of the essential issues for spacecraft is maintaining the combustion chamber wall from
exceeding acceptable temperatures. The cooling channels' thermal resistance and flow …

In this work an efficient numerical framework for the prediction of wall heat loads in Liquid
Rocket Engine combustion chambers is presented. The proposed framework is based on a …

For rocket cycles involving electric pumps, gas generators, expanders, and staged
combustion, a thermal recycling method is proposed to provide a more realistic simulation of …

Regenerative cooling is widely used in high-pressure and high-thrust fuel-cooled rocket
engines, also suitable for hypersonic structures. The propellant duality in terms of functions …

The current work presents the extension of the flamelet model for turbulent combustion
calculations to account for deviations from adiabatic conditions. The aforementioned …

The design phase of a rocket combustion chamber relies on the prediction of the wall heat
fluxes, in order to optimize the components to prevent thermal damage. Based on the …

The present work is motivated to develop a unified framework to simulate multi-physical
processes which are crucial for trade-off design of liquid rocket thrust chambers among …

The supersonic split line (SSSL) nozzle is one of the thrust vector nozzles. Because of the
complex internal flow, designing a high-performance SSSL nozzle, especially with a large …