Experimental studies have been conducted to obtain detailed measurements of heat transfer and pressure in laminar regions of shock-induced separated flow over a hollow cylinder/flare and double cone configurations in hypervelocity flows at zero incidence in low density flows, and for 2.5° incidence in continuum flows to provide code validation data for DSMC and Na vier-Stokes methods respectively. In addition, heat transfer measurements were made on cylinders and hemispheres at Reynolds numbers down to 100 to evaluate the DSMC predictions for stagnation heating. The experimental programs were conducted in nitrogen and air for a Mach number range from 10 to 12 with Reynolds numbers from 1 × 104 to 5 × 105 and velocities between 7,000 to 9,000 ft/sec. Miniature high-frequency thin-film and piezoelectric instrumentation was employed to obtain the high spatial resolution required to accurately define the distribution of heat transfer and pressure in the strong gradients which occur in regions of shear layer reattachment and shock/shock interaction. The computations presented here are a more highly refined version of those performed earlier in the "blind" validation exercise, accounting for the effects of vibrational nonequilibrium in the nitrogen nozzle flow and vibrational slip over the models. The comparisons between prediction and experiment were even more impressive than the previous efforts demonstrating that carefully performed calculations of both the flow in the nozzle and over the model can predict even the most complex laminar interactions in hypervelocity flows in the presence of vibrational nonequilibrium in the nitrogen flow.