What is it about?
Supersonic wind tunnel experiments have been conducted with a Mach 4 laminar boundary layer. Various angles of ramps have been investigated to assess shock boundary layer interactions at different Reynolds numbers and with different strengths. Mid-interaction transition was observed in strong high-Reynolds number configurations and analyzed further with high-speed schlieren. Density disturbances identified in the separated flow were shown to directly influence the unsteady separation shock motion, with negligible influence from upstream.
Photo by Mathew Schwartz on Unsplash
Read the Original
This page is a summary of: Transitional Shock Boundary Layer Interactions on a Compression Ramp at Mach 4, AIAA Journal, December 2021, American Institute of Aeronautics and Astronautics (AIAA), DOI: 10.2514/1.j059981.
You can read the full text:
The following have contributed to this page