NUMERICAL SIMULATIONS OF THE INFLUENCE OF VARIOUS PARAMETERS ON HEAT TRANSFER AND FLOW SEPARATION IN SUPERSONIC COOLED NOZZLES
In rocket engine nozzle design, flow separation is essential and, given the high temperatures and pressures in the thrust chamber, regenerative cooling is critical for maintaining the nozzle wall's integrity. This passage provides a summary of an in-depth numerical analysis of boundary layer separation and heat transfer within a 30°-15&A...
By Bensayah Khaled, Kamri Khadidja
NUMERICAL INVESTIGATION OF SUPERSONIC FLOW SEPARATION IN THRUST-OPTIMIZED CONTOUR ROCKET NOZZLE
The difficulties associated with thrust-optimized contour nozzles have led to significant advances in our knowledge of the physical phenomena associated with flow separation. In this study, a fully implicit scheme is implemented using a combined weight function for splitting the flux to analyze the shock patterns in the optimized contour (TOC) that...
By Bensayah Khaled, Kamri Khadidja