As part of a two-phase experimental study to obtain detailed heating and pressure data over the full-scale hypersonic international flight research and experimentation (HIFiRE-1, formally FRESH FX-1) flight geometry, Calspan-University at Buffalo Research Center has completed a matrix of ground tests to determine the optimal flight geometry and instrumentation configuration necessary to make measurements of desired flow phenomena during the flight experiment. The primary objective of the HIFiRE-1 flight experiment is to collect high-quality flight data from integrated flight instrumentation to be used for computational fluid dynamic code and ground test facility validation in regions of boundary-layer transition, turbulent separated flow, and shock/boundary-layer interaction. To support this flight experiment, data have been obtained in the large energy national shock hypervelocity wind tunnel employing a full-scale model over a range of Mach numbers from 6.5 to 7.4 and Reynolds numbers from 0:5E 06 to 5:5E 6 duplicating the reentry trajectory. These points gave researchers the best chance to measure the transition process on the forecone and have a turbulent separated flow on the cylinder that reattached onto the flare section. These test condition ranges were determined directly from the nominal descent trajectory of the Australian-launched Terrier-Orion launch vehicle that will serve as the booster for HIFiRE-1. The entire experimental database will be compared to future flight data and used by computationalists to validate codes in regions of attached and separated laminar and turbulent flows with shock/boundary layer interaction. In addition to the experimental data, Calspan-University at Buffalo Research Center performed a large amount of computational fluid dynamic analyses to confirm and validate not only the tunnel flow conditions, but also the two-and threedimensional flows over the model itself. These detailed computational results will be presented in a Part 2 companion paper.

Detailed surface heat transfer and pressure measurements have been made in laminar separated regions of shock wave/boundary layer interaction in high-enthalpy flows over double cone and hollow cylinder/flare configurations to provide data sets with well-defined boundary conditions for comparison with Navier-Stokes computations including the effects of nonequilibrium air chemistry. In these experimental studies, which were conducted in the LENS I and XX shock/expansion tunnels, measurements were made in air, nitrogen, and oxygen for a range of Reynolds number conditions at velocities from 8,000 to 22,000 ft/s to provide measurements with which to evaluate the models of real gas chemistry employed in Navier-Stokes codes. Flowfield measurements have been made with high-speed Schlieren photography and interferometry to provide additional measurements to define the size and structure of the separated interaction region. Details of the model configurations and the freestream conditions at which these studies have been conducted, together with earlier measurements and measurements upstream of the interaction regions are presented in this paper to enable computations to be performed with both Navier-Stokes and DSMC prediction methods for "blind comparisons" with the experimental data. These comparisons will be presented at an AIAA meeting during the coming year.

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