Measurements in Regions of Shock Wave/Turbulent Boundary Layer Interaction from Mach 3 to 10 for Open and Blind Code Evaluation/Validation

Experimental studies have been conducted to examine the characteristics of regions of shock wave/turbulent boundary layer interaction over cone/flare and hollow cylinder/flare configurations in high Reynolds number flows at Mach numbers between 5 and 10 in cold flows and in flows with duplicated flight velocities. Detailed surface pressure and heat transfer measurements have been made through the separated interaction regions as well as upstream and downstream of the interactions for a range of Reynolds numbers under cold wall conditions for total enthalpies duplicating flight. The large scale of the models used in these experiments enabled us to obtain measurements in fully turbulent flows with the length of turbulent flow up to 1,000 boundary layer thicknesses downstream of the beginning of untripped transition. The surface measurements obtained in these studies together with Schlieren and interferometry measurements of the regions of shock wave/boundary layer interaction have been assembled to provide data sets for blind code validation studies. The original document contains color images.