Mach-4 supersonic-intake shock-wave / boundary-layer transition case study computed with the UniSTAR-CFD solver, validated against three real experimental benchmarks.
python validation scientific-computing cfd computational-fluid-dynamics supersonic aerospace-engineering hypersonic rans shock-waves aerothermodynamics turbulence-modeling shock-wave-boundary-layer-interaction swbli boundary-layer-transition supersonic-intake
-
Updated
Jun 30, 2026 - Python