Shock-boundary-layer interaction in a supersonic inlet
Density-based compressible RANS resolving the oblique shock train and separation bubble in a supersonic intake, with mesh convergence checked against a CABARET benchmark run.
Problem
A supersonic inlet design needed the shock train and any associated boundary-layer separation characterised across its Mach operating range, since separation there drives distortion at the engine face.
Approach
Density-based compressible RANS resolved the oblique shock train and the shock-induced separation bubble, with grid convergence cross-checked against a high-order CABARET run to confirm the shock capturing wasn't an artefact of numerical dissipation in the primary solver.
Outcome
The separation bubble extent and its sensitivity to back-pressure were mapped across the Mach range, giving the client the distortion input needed for the engine-face compatibility assessment.
// CANONICAL REFERENCES
The literature behind this run
- Délery, J. (1985). Shock Wave/Turbulent Boundary Layer Interaction and Its Control. Progress in Aerospace Sciences, 22(4)
- Dolling, D. S. (2001). Fifty Years of Shock-Wave/Boundary-Layer Interaction Research: What Next?. AIAA Journal, 39(8)
- Green, J. E. (1970). Interactions Between Shock Waves and Turbulent Boundary Layers. Progress in Aerospace Sciences, 11
These are the foundational papers the underlying method or validation approach is built on — not client deliverables. Full citation details are provided so the physics can be checked independently.
Have a similar geometry or flow regime? We'll scope the mesh and turnaround.
Start a project