DescriptionFor assessment of CFD capability in the prediction of the aerothermodynamic loading on a hypersonic shock wave boundary layer interaction (SWBLI) region, the numerical simulation of hypersonic laminar flow over a blunt cone flare configuration is performed using the perfect gas laminar Navier-Stokes equations. Computational results are compared with experimental data measured by Infrared Thermography technology from the US Air Force Research Lab's Mach 6 Ludwieg Tube wind tunnel. Heat transfer data from the simulation agrees well with the experiment upstream of the SWBLI region but the separation zone is overpredicted in all computational cases, suggesting that the experimental data does not converge to steady state.