| _version_ | 1866901698423816192 |
|---|---|
| author | Dr. Jayahar Sivasubramanian Nishma K B |
| author_facet | Dr. Jayahar Sivasubramanian Nishma K B |
| contents | Shock wave boundary layer interaction (SWBLI) is a key phenomenon in high-speed aerodynamics, influencing aerodynamic efficiency, stability, and thermal loading. This study employs the SU2 solver to investigate SWBLI in laminar and turbulent regimes. Initially, two-dimensional turbulent cases for three different wedge angles are validated against experimental data to ensure numerical accuracy. The analysis then focuses on laminar interactions, where low-momentum boundary layers are more susceptible to shock-induced adverse pressure gradients, leading to flow separation, recirculation bubbles, and delayed recovery. Reynolds number effects are examined by systematically reducing freestream pressure, thereby altering both shock strength and viscous properties. Results indicate that lower Reynolds numbers generate weaker shocks and shorter separation bubbles with earlier reattachment, whereas higher Reynolds numbers produce stronger shocks, longer bubbles, and delayed reattachment despite higher boundary layer resistance. The study highlights the coupled influence of Reynolds number and freestream conditions on laminar SWBLI, providing insights that enhance predictive capability for high-speed vehicle design and optimization. To ensure accuracy, the study begins with validating turbulent 2D simulations against experimental data using the SU2 solver. After validation, laminar cases are examined to understand how the nature of the boundary layer affects interaction strength, separation, and pressure distribution. In the present study, a computational investigation of shock wave Laminar and turbulent boundary layer interaction is carried out using the open-source CFD solver SU2. The configuration involves an oblique shock generated by a wedge impinging on a flat plate, representing a canonical SWBLI case. Three wedge angles 6°, 10°, and 14° are considered to examine their influence on surface pressure, skin friction, and heat flux distributions. The numerical results are validated against the experimental data of [13] to assess the predictive capability of turbulence models in SU2. This study underscores the limitations of existing models in capturing shock-induced separation and highlights the need for accurate numerical modelling in high-speed aerodynamic design. |
| format | Recurso digital |
| id | zenodo_https___doi_org_10_5281_zenodo_19569688 |
| institution | Zenodo |
| language | |
| publishDate | 2026 |
| publisher | Zenodo |
| record_format | zenodo |
| spellingShingle | Computational Study of Laminar and Turbulent Shock Wave Boundary Layer Interactions at Mach 5 Dr. Jayahar Sivasubramanian Nishma K B SWBLI Laminar Turbulent Separation Bubble Shock wave boundary layer interaction (SWBLI) is a key phenomenon in high-speed aerodynamics, influencing aerodynamic efficiency, stability, and thermal loading. This study employs the SU2 solver to investigate SWBLI in laminar and turbulent regimes. Initially, two-dimensional turbulent cases for three different wedge angles are validated against experimental data to ensure numerical accuracy. The analysis then focuses on laminar interactions, where low-momentum boundary layers are more susceptible to shock-induced adverse pressure gradients, leading to flow separation, recirculation bubbles, and delayed recovery. Reynolds number effects are examined by systematically reducing freestream pressure, thereby altering both shock strength and viscous properties. Results indicate that lower Reynolds numbers generate weaker shocks and shorter separation bubbles with earlier reattachment, whereas higher Reynolds numbers produce stronger shocks, longer bubbles, and delayed reattachment despite higher boundary layer resistance. The study highlights the coupled influence of Reynolds number and freestream conditions on laminar SWBLI, providing insights that enhance predictive capability for high-speed vehicle design and optimization. To ensure accuracy, the study begins with validating turbulent 2D simulations against experimental data using the SU2 solver. After validation, laminar cases are examined to understand how the nature of the boundary layer affects interaction strength, separation, and pressure distribution. In the present study, a computational investigation of shock wave Laminar and turbulent boundary layer interaction is carried out using the open-source CFD solver SU2. The configuration involves an oblique shock generated by a wedge impinging on a flat plate, representing a canonical SWBLI case. Three wedge angles 6°, 10°, and 14° are considered to examine their influence on surface pressure, skin friction, and heat flux distributions. The numerical results are validated against the experimental data of [13] to assess the predictive capability of turbulence models in SU2. This study underscores the limitations of existing models in capturing shock-induced separation and highlights the need for accurate numerical modelling in high-speed aerodynamic design. |
| title | Computational Study of Laminar and Turbulent Shock Wave Boundary Layer Interactions at Mach 5 |
| topic | SWBLI Laminar Turbulent Separation Bubble |
| url | https://doi.org/10.5281/zenodo.19569688 |