Scramjet Inlet CFD Validation Help (Hypersonic)

I have already built and run a three-ramp scramjet inlet with an isolator in ANSYS Fluent for a freestream Mach of 6.8 at 300 K. The geometry and test conditions follow the reference study you will find here:
https://www.mediafire.com/file/114w1th29a8pqyf/Impact+of+wall+cooling+on+the+stability+and+aerothermodynamic+performance+of+a+scramjet+inlet.pdf/file

Although the solution reaches convergence, the peak coefficient of pressure is roughly 30 % lower than the paper reports, and the mass-flow prediction drifts in the same range. I am using the density-based solver, ideal-gas properties, and the SST-Transition turbulence model; wall cooling is included exactly as described in the article. Mesh quality looks acceptable on standard checks, yet the mismatch persists.

What I need from you is a focused second look at the entire setup—boundary conditions, mesh strategy, turbulence and energy settings, viscous heating, wall-function treatment, and any discretisation or solver parameters that could explain the deviation. A brief, well-reasoned memo or annotated case file that brings my results to within ±5 % of the published Cp peak will close the job. If you prefer to start from scratch with your own grid or recommend OpenFOAM cross-checks, that is fine, but the final answer must still run in Fluent.

Please let me know what additional files you require and how long you expect the troubleshooting and validation cycle to take so we can lock the milestones.