Measurements in laminar regions of shock/shock and shock/boundary layer interaction over cylindrical leading edges, cone/cone and hollow cylinder flare configurations for DSMC/Navier-Stokes code validation

Detailed measurements of the distribution of heat transfer and pressure, as well as Schlieren photographs, have been obtained in a series of experimental studies designed to provide measurements with which to evaluate the capabilities of the current numerical simulation techniques to predict the detailed characteristics of regions of shock/shock and shock/boundary layer interactions in laminar hypersonic flows. These experimental studies were conducted for a range of Mach numbers and Reynolds numbers to obtain fully laminar flows at conditions through the interaction regions that could be predicted with both DSMC and Navier-Stokes numerical schemes. In the first part of this paper, we present the model configuration, test condition and surface and flowfield measurements obtained in regions of shock/shock interaction over a highly instrumented cylindrical leading edge. In part two, only the model configurations, test conditions, and sample surface measurements are presented on two models—an axisymmetric cone/cone and a hollow cylinder flare configuration. The measurements that have been made on these configurations are being retained until the results of predictions with the DSMC and Navier-Stokes codes have been completed.