Examined is sensitivity of separation extent, wall pressure and heating to variation of primary input flow parameters, such as Mach and Reynolds numbers and shock strength, for 2D and Axisymmetric Hypersonic Shock Wave Turbulent Boundary Layer interactions obtained by Navier-Stokes methods using the SST turbulence model. Baseline parametric sensitivity response is provided in part by comparison with vetted experiments, and in part through updated correlations based on free interaction theory concepts. A recent database compilation of hypersonic 2D shock-wave/turbulent boundary layer experiments extensively used in a prior related uncertainty analysis provides the foundation for this updated correlation approach, as well as for more conventional validation. The primary CFD method for this work is DPLR, one of NASA's real-gas aerothermodynamic production RANS codes. Comparisons are also made with CFL3D, one of NASA's mature perfect-gas RANS codes. Deficiencies in predicted separation response of RANS/SST solutions to parametric variations of test conditions are summarized, along with recommendations as to future turbulence approach. Brown, James L. Ames Research Center NASA/TM-2014-218353, ARC-E-DAA-TN15380 NAVIER-STOKES EQUATION; TURBULENCE MODELS; COMPUTATIONAL FLUID DYNAMICS; HYPERSONIC SHOCK; BOUNDARY LAYER SEPARATION; MACH NUMBER; REYNOLDS NUMBER; AEROTHERMODYNAMICS; WALL PRESSURE; SHOCK WAVE INTERACTION; PRESSURE DISTRIBUTION