Stability of Hypersonic Boundary Layers on Flat Plates with Sharp and Blunt Leading Edges 2024-26-0457

This research employs a comprehensive methodology to explore hypersonic boundary layers' stability and transition dynamics, focusing specifically on the influence of sharp and blunt leading edges. The Stanford University Unstructured (SU2) Computational Fluid Dynamics (CFD) solver is utilized 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. Further analysis is conducted using a Python code to generate input files for the Linear Stability Solver. The Linear Stability Solver analysis constitutes a crucial phase wherein the research delves into the eigenvalue spectra, identifying dominant modes and closely scrutinizing the role of the modes in the transition process within the hypersonic boundary layers. This investigation into stability characteristics is paramount for designing and optimizing hypersonic vehicles, providing valuable insights to enhance their efficiency and performance. 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.