Abstract

This study presents a comprehensive review of the study entitled Passive Control of Base Flow at Sonic and Supersonic Mach Numbers. The research investigates passive flow control techniques to improve base pressure and reduce aerodynamic drag in suddenly expanded flows. Base drag significantly contributes to the overall drag experienced by high-speed aerospace vehicles such as rockets, missiles, and aircraft. The study employs Computational Fluid Dynamics (CFD) to analyze the effects of cavity-based passive control devices under various nozzle pressure ratios and flow conditions. The results show that introducing cavities can modify the recirculation region behind the nozzle exit, increasing base pressure and potentially reducing drag. This review examines the study’s research objectives, methodology, findings, and engineering significance. It also critically evaluates the research’s strengths and limitations. Overall, the study contributes valuable insights into passive flow control techniques and provides a foundation for future investigations into drag reduction technologies for aerospace applications.

Keywords

aerospace, base flow, mach number, fluid dynamics, nozzle pressure