Numerical analysis of transonic

The objective of this research is to investigate a flow structure in subsonic and transonic configurations for applications in aerospace propulsion. This plays a critical role in determining flow separation, pressure losses, and overall efficiency in many configurations. The study will use high-fidelity CFD simulations to analyze the behavior of shock-induced boundary layer separation under various flow conditions and geometries representative of engine inlets. A particular focus will be placed on capturing the unsteady characteristics of the interaction and its sensitivity to changes in Mach number and Reynolds number. The results will support the development of more efficient and stable propulsion systems by providing insight into shock control strategies and flow conditioning techniques. The simulations will be carried out using validated turbulence models such as SST k–ω or EARSM, and may be supplemented with literature-based validation cases or experiments where applicable.
This project aims to investigate a flow structure in subsonic and transonic configurations for applications in aerospace propulsion. These flow features are critical in determining the efficiency, stability, and performance of turbomachinery cascades and engine inlets. Using advanced CFD tools, including OpenFOAM, ANSYS Fluent, STAR-CCM+, and Cadence FineOpen/FineTurbo, the research will analyze flow separation, shock-induced transition, and unsteady phenomena in engine inlet geometries. The results will support the design of more efficient propulsion systems and contribute to the development of accurate numerical models for compressible turbulent flows.