Stability of Hypersonic Boundary Layers on Flat Plates with Sharp and Blunt Leading Edges

This research employs a comprehensive methodology to explore the stability and transition dynamics of hypersonic boundary layers, focusing specifically on the influence of sharp and blunt leading edges. The Stanford University Unstructured (SU2) Computational Fluid Dynamics (CFD) solver is utilised to compute the mean flow over a flat plate, establishing a foundational basis for subsequent stability analysis. The extracted boundary layer profiles undergo validation against existing literature, ensuring accuracy and reliability. The linear stability Solver analysis constitutes a crucial phase wherein the research focuses on the eigenvalue spectra, identifying dominant modes and closely scrutinising the transition process within the hypersonic boundary layers. This investigation into stability characteristics is paramount for designing and optimising hypersonic vehicles, providing valuable insights to enhance their efficiency and security. By comprehending the intricate interplay between sharp and blunt leading edges and stability, the research contributes to formulating predictive models, simulations, and control strategies. These strategies aim to mitigate the disruptive effects of instability, ultimately elevating hypersonic vehicles' overall performance and safety. The study's outcomes advance our understanding of the complex relationship between the radius of leading edges and hypersonic boundary layer stability and pave the way for tangible advancements in hypersonic vehicle design and operation, offering valuable contributions to developing safer and more efficient hypersonic vehicles.